Faculty Profiles - KOUCHI Toshinori

写真a

KOUCHI Toshinori

Organization

Faculty of Environmental, Life, Natural Science and Technology Professor

Homepage

http://db.tohoku.ac.jp/whois/detail/cd61a580392a70389e27b0bc2b439f49.html

External link

Degree

博士（工学） ( 2005.3 東北大学 )

Research Interests

航空宇宙工学
超音速流
空気力学
高レイノルズ数
先進レーザ計測
スクラムジェット

Research Areas

Manufacturing Technology (Mechanical Engineering, Electrical and Electronic Engineering, Chemical Engineering) / Thermal engineering
Frontier Technology (Aerospace Engineering, Marine and Maritime Engineering) / Aerospace engineering
Manufacturing Technology (Mechanical Engineering, Electrical and Electronic Engineering, Chemical Engineering) / Fluid engineering

Education

Tohoku University 工学研究科航空宇宙工学専攻

- 2005

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Country： Japan

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Tohoku University 工学研究科航空宇宙工学専攻

- 2003

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Country： Japan

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Research History

Okayama University, Natural Science and Technology, Mechanical and Systems Engineering, Fluid Dynamics Professor

2020.4

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Okayama University, Natural Science and Technology, Mechanical and Systems Engineering, Fluid Dynamics Associate Professor

2012.9 - 2020.3

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Tohoku University Graduate School of Engineering, Department of Aerospace Engineering, Aerospace Systems Assistant Professor

2007.6 - 2012.8

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Japan Aerospace Exploration Agency

2005 - 2007

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東北大学日本学術振興会特別研究員

2003 - 2005

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Professional Memberships

日本航空宇宙学会

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日本機械学会

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日本流体力学会

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Committee Memberships

日本流体力学会理事

2023.4

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日本流体力学会代議委員

2021.4

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日本機械学会中四国支部商議員

2021.4

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Committee type：Academic society

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日本機械学会中四国支部幹事（岡山地区）

2021.4 - 2023.3

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Committee type：Academic society

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日本燃焼学会調査研究「超音速燃焼」小委員会委員

2020.9 - 2021.3

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Committee type：Academic society

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日本学術振興会科学研究費委員会専門委員審査第二部会第24010小委員会

2018.12 - 2019.11

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Committee type：Academic society

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日本機械学会流体工学部門運営委員会委員

2018.4 - 2020.3

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Committee type：Academic society

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Papers

Examining eddy viscosity based LES analyses using low to moderate Reynolds number free stream turbulence due to anisotropic forcing Reviewed

Hiroki Suzuki, Shinsuke Mochizuki, Toshinori Kouchi

Theoretical and Applied Mechanics Letters 2025.9

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Authorship：Last author Language：English Publishing type：Research paper (scientific journal)

DOI： 10.1016/j.taml.2025.100615

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Application of a direct Poisson solver for the analysis of incompressible flow in a floating stage Reviewed

Hiroaki Oka, Hiroki Suzuki, Jun Fujiwara, Toshinori Kouchi

Journal of Physics: Conference Series 3027 ( 1 ) 012071 - 012071 2025.6

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Language：English Publishing type：Research paper (scientific journal) Publisher：IOP Publishing

Abstract

This study investigates the application and effectiveness of a direct method for solving the Poisson equation in the analysis of low Reynolds number flows within a floating stage. To efficiently analyze a turbulent flow field with periodic boundary conditions in two directions, a direct method is applied to the Poisson equation. In low Reynolds number cases, the effect of non-zero velocity divergence as an error increases as the Reynolds number decreases, manifesting itself as an error in the divergence of the viscous term. Therefore, for low Reynolds number flows, it is essential to minimize the velocity divergence as much as possible. In this study, the applicability of the direct method for solving the Poisson equation is first validated in an inviscid flow field. It is then applied to analyze the flow field in the floating stage as an example of a low Reynolds number flow. The results demonstrate the effectiveness of the direct method for solving the Poisson equation by comparing it with an iterative method.

DOI： 10.1088/1742-6596/3027/1/012071

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Other Link： https://iopscience.iop.org/article/10.1088/1742-6596/3027/1/012071/pdf
Fundamental examination of coherent structure model prediction using vortex cores in a two-dimensional Taylor’s analytical solution Reviewed

Xuanyou Gong, Hiroki Suzuki, Toshinori Kouchi, Kento Tanaka

Journal of Physics: Conference Series 3027 ( 1 ) 012008 - 012008 2025.6

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Language：English Publishing type：Research paper (scientific journal) Publisher：IOP Publishing

Abstract

This study focuses on the possibility that flow around vortex tubes in turbulence may resemble laminar flow, and aims to describe the characteristics of turbulent fields using analytical solutions to the governing equations. In the two-dimensional analytical Taylor solution, the velocity and pressure fields are expressed by trigonometric functions, and a structure in which counter-rotating vortices are arranged in a grid pattern is demonstrated. This solution is used to verify the accuracy of numerical analyses and is expected to contribute to a simple yet unambiguous description of turbulent fields based on vortex structures. Predictions of sub-grid scale components and validation of a coherent structure model using invariants of the velocity gradient tensor are also performed.

DOI： 10.1088/1742-6596/3027/1/012008

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Other Link： https://iopscience.iop.org/article/10.1088/1742-6596/3027/1/012008/pdf
LES analysis to investigate a random-phase forcing scheme for steadying anisotropic turbulence fields Reviewed

Koki Minami, Hiroki Suzuki, Toshinori Kouchi, Kento Tanaka

Journal of Physics: Conference Series 3027 ( 1 ) 012009 - 012009 2025.6

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Language：English Publishing type：Research paper (scientific journal) Publisher：IOP Publishing

Abstract

The aim of this study is to investigate the effect of phase randomization on forcing mechanisms that stabilize localized turbulence. A trigonometric forcing based on vector potential is combined with uniform random numbers to create a spatially homogeneous forcing field. The analysis is performed using large-eddy simulation (LES) with the Smagorinsky model as the subgrid scale model. The results demonstrate that steady flows are generated regardless of the presence of phase randomization, successfully forming isotropic turbulence. In contrast, for anisotropic turbulent fields, the addition of phase randomization reduces the degree of anisotropy, indicating a smoothing effect on the anisotropy of the flow.

DOI： 10.1088/1742-6596/3027/1/012009

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Other Link： https://iopscience.iop.org/article/10.1088/1742-6596/3027/1/012009/pdf
Spherical shock wave modulation induced by interaction with homogeneous isotropic turbulence Reviewed

K. Tanaka, T. Watanabe, H. Suzuki, T. Kouchi

Physics of Fluids 2025.2

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Language：English Publishing type：Research paper (scientific journal)

DOI： 10.1063/5.0249098

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CNN Model to Predict Wall Shear Stress From Flow Velocity Data Without Viscous Sub-Layer

Kazuki Naridomi, Toshinori Kouchi, Kento Tanaka

AIAA Scitech2025 2025.1

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Language：English Publishing type：Research paper (international conference proceedings)

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Investigation of Instantaneous Velocity-Fields by Schlieren Image Velocimetry Using Ray-Traced Simulated Focusing-Schlieren Images

Toshinori Kouchi, Narumi Kodera, Kento Tanaka, Hiroki Suzuki

AIAA Scitech2025 2025.1

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Authorship：Lead author Language：English Publishing type：Research paper (international conference proceedings)

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Examining OpenFOAM-based LES analysis in terms of inviscid energy conservation and viscous turbulence decay Reviewed

Hiroki Suzuki, Shisuke Mochizuki, Toshinori Kouchi

Mechanical Engineering Journal 2025

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Authorship：Last author Language：English Publishing type：Research paper (scientific journal)

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Numerical analysis validating the standard k-epsilon model for the kinetic energy of turbulence subjected to weak but long-lasting wind tunnel blockage acceleration Reviewed

Akira ONO, Hiroki SUZUKI, Toshinori KOUCHI, Kento TANAKA

Journal of Fluid Science and Technology 20 ( 1 ) JFST0004 - JFST0004 2025

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Language：English Publishing type：Research paper (scientific journal) Publisher：Japan Society of Mechanical Engineers

DOI： 10.1299/jfst.2025jfst0004

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主流乱れと乱流境界層の混合流れ場生成のための流入境界条件の検討 Reviewed

田中健人, 鈴木智也, 鈴木博貴, 河内俊憲

日本航空宇宙学会論文集 2025

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Authorship：Last author Language：Japanese Publishing type：Research paper (scientific journal)

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RANS Model-based Constant Temperature Anemometry Examination to Validate Negligible Wind Tunnel Blockage Effect on Developed Multi-scale Generated Grid Turbulence Reviewed

Keita Nakamura, Hiroki Suzuki, Toshinori Kouchi, Kento Tanaka

2024 3rd International Conference on Automation, Robotics and Computer Engineering (ICARCE) 453 - 457 2024.12

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Language：English Publishing type：Research paper (international conference proceedings) Publisher：IEEE

DOI： 10.1109/icarce63054.2024.00092

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Numerical Analysis of a Low Reynolds Number Flow in a Non-Contact Air Stage Validated through Time Increment Width Testing Reviewed

Hiroaki Oka, Hiroki Suzuki, Jun Fujiwara, Toshinori Kouchi

Proceedings of the 12th JFPS International Symposium on Fluid Power P2-21 2024.10

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Language：English Publishing type：Research paper (international conference proceedings)

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Attempt to compensate for effects of energy conservation error on static pressure fluctuation using sub-grid scale components with the Reynolds number dependence of isotropic/anisotropic steady turbulence Reviewed

Makoto Chitose, Hiroki Suzuki, Toshinori Kouchi

Journal of Physics: Conference Series 2793 ( 1 ) 012004 - 012004 2024.7

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Publishing type：Research paper (scientific journal) Publisher：IOP Publishing

Abstract

This study focuses on the kinetic energy conservation error and the compensation effect by adjusting a model constant. The kinetic energy conservation error is caused by the implicit time integration of the second-order Crank-Nicholson method, and we investigate how much this error affects the RMS of the static pressure fluctuation. Anisotropic and isotropic external force terms are used to generate a steady turbulent flow field, and the numerical analysis employs Large Eddy Simulation (LES) and the Smagorinsky model. Studies have shown that the influence of kinetic energy conservation errors on turbulent kinetic energy is limited, but large-scale turbulent structures are affected by errors in anisotropic turbulent fields with large Re numbers. Ta. Regarding the compensation of the RMS of the static pressure fluctuation, it was shown that the error could be reduced in both isotropic and anisotropic fields by adjusting the model constant, but there was a clear difference for the turbulent kinetic energy. This result shows that the compensation of kinetic energy conservation errors by a model constant is not perfect and that the errors can have different effects on the turbulence statistics.

DOI： 10.1088/1742-6596/2793/1/012004

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Other Link： https://iopscience.iop.org/article/10.1088/1742-6596/2793/1/012004/pdf
Numerical analysis clarifying non-equilibrated periodic flows generated by dual-scaling Taylor’s analytical solution Reviewed

Xuanyou Gong, Hiroki Suzuki, Toshinori Kouchi

Journal of Physics: Conference Series 2793 ( 1 ) 012001 - 012001 2024.7

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Publishing type：Research paper (scientific journal) Publisher：IOP Publishing

Abstract

This study investigates the properties of a flow field derived from the multiplexed Taylor solution, focusing on its impact on established equilibrium relationships. We numerically analyse a multiplexed flow field by introducing a secondary flow with twice the period of the original Taylor solution, hypothesising that this dualisation affects the balance between transient and viscous terms. The visualisation of the flow field and the time evolution of the kinetic energy are investigated. Using second and sixth order central differences and the fractional step method with BiCGStab, we analyse three flow fields with different coefficients in a two-dimensional periodic domain. The study shows that the dualisation of the flow field disturbs the equilibrium between the unsteady and viscous terms. The time-averaged kinetic energy shows that the evolution of the dualised field approaches the kinetic energy distribution of the analytical solution, with variations depending on the coefficient of the quadratic term. The spatial distribution of the kinetic energy in fully developed fields is also compared with the analytical solution.

DOI： 10.1088/1742-6596/2793/1/012001

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Other Link： https://iopscience.iop.org/article/10.1088/1742-6596/2793/1/012001/pdf
LES Analysis on the Impact of Mass Conservation Uncertainty on the Static Pressure Fluctuation in Spatially Periodic Steady Turbulence Reviewed

Xuanyou Gong, Hiroki Suzuki, Mikio Nakahama, Toshinori Kouchi

2023 2nd International Conference on Automation, Robotics and Computer Engineering (ICARCE) 1 - 5 2024.4

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Publishing type：Research paper (international conference proceedings) Publisher：IEEE

DOI： 10.1109/icarce59252.2024.10492603

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CTA Measurement on the Frequency Response of a Grid Turbulence Fluctuation Measurement with a Focus on Bispectrum Reviewed

Hiroto Yamaguchi, Hiroki Suzuki, Kyosuke Fujita, Toshinori Kouchi

2023 2nd International Conference on Automation, Robotics and Computer Engineering (ICARCE) 1 1 - 6 2024.4

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Publishing type：Research paper (international conference proceedings) Publisher：IEEE

DOI： 10.1109/icarce59252.2024.10492576

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Non-linear response of kinetic energy in an inviscid Taylor-Green flow obtained by OpenFOAM-LES with respect to time increments Reviewed

Akira Ono, Hiroki Suzuki, Toshinori Kouchi

Journal of Physics: Conference Series 2701 ( 1 ) 012054 - 012054 2024.2

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Publishing type：Research paper (scientific journal) Publisher：IOP Publishing

Abstract

This study investigates the conservation error of kinetic energy with respect to time increment using OpenFOAM LES. The energy conservation error is verified using an inviscid Taylor-Green vortex and the effect on energy conservation is checked by varying the time increment by a factor of 30. Differences in the response of turbulent energy conservation between large and small time increments are also verified. Higher order accuracy for time increments is expected when the kinetic energy conservation accuracy is high, however the actual behaviour in OpenFOAM needs to be investigated: as the implicit time integration method is used in OpenFOAM, a non-linear response is expected. As a result, it is evident that kinetic energy is not fully conserved in the inviscid flow of OpenFOAM. The kinetic energy distribution is similar for different time increments, with a different relationship between the conservation error observed in the range of large and small time increments.

DOI： 10.1088/1742-6596/2701/1/012054

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Other Link： https://iopscience.iop.org/article/10.1088/1742-6596/2701/1/012054/pdf
Energy conservation uncertainly due to the use of an implicit time integration method clarified by a multiplexed TGV inviscid flow Reviewed

Makoto Chitose, Hiroki Suzuki, Toshinori Kouchi

Journal of Physics: Conference Series 2701 ( 1 ) 012059 - 012059 2024.2

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Publishing type：Research paper (scientific journal) Publisher：IOP Publishing

Abstract

This study attempts to elucidate the conservation errors induced by the implicit time integration method within a multiscale flow. Using the multiplexed Taylor analytical solution as the initial field, three distinct multiscale turbulence fields were formulated, each characterised by different wavenumber attributes. A two-dimensional inviscid flow field, replicated in a computational domain with a side of 2π and subject to periodic boundary conditions, was used to illuminate kinetic energy conservation errors. The implicit time integration method - specifically the second-order accurate Crank-Nicolson method - was compared with explicit methods, such as the second-order accurate Adams-Bashforth and third-order accurate Runge-Kutta methods. The study also examines the differences between the analytical Taylor solution and a random flow field, particularly in their satisfaction of the Navier-Stokes equations and wavenumber composition, while highlighting the need for preliminary analysis for random flow fields prior to validation calculations.

DOI： 10.1088/1742-6596/2701/1/012059

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Other Link： https://iopscience.iop.org/article/10.1088/1742-6596/2701/1/012059/pdf
Multiscaled inviscid Taylor-Green vortex flow for examining energy conservation error in incompressible flows Reviewed

Xuanyou Gong, Hiroki Suzuki, Toshinori Kouchi

Journal of Physics: Conference Series 2701 ( 1 ) 012052 - 012052 2024.2

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Publishing type：Research paper (scientific journal) Publisher：IOP Publishing

Abstract

This study investigates kinetic energy conservation errors in incompressible flows using multiplexed inviscid Taylor-Green vortices. Fourth-order precision Runge-Kutta methods, specifically five- and six-step methods, were employed and an inviscid two-dimensional periodic flow field was used as a test case. This method allows the energy conservation error to be suppressed to a very low level. Recent previous studies have dealt with turbulence generation using a multi-scale turbulence grid. In this study, the Taylor-Green vortex of the analytical solution is multiplexed to generate a flow field with a number of wavenumbers. Visualisation results of the initial field and the energy distribution over time were obtained. It was observed that the errors in the time evolution of the fluid energy were extremely small, and that the errors actually increased with time. However, the influence of the time step range was limited and the analytical and numerical solutions were in general agreement. As a result, it was confirmed that the inviscid Taylor-Green vortex is effective in examining the energy conservation error for incompressible flows.

DOI： 10.1088/1742-6596/2701/1/012052

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Other Link： https://iopscience.iop.org/article/10.1088/1742-6596/2701/1/012052/pdf
Experimental validation on a calibration position of a hot-wire anemometer for measuring multi-scale grid-generated turbulence Reviewed

Hiroto Yamaguchi, Hiroki Suzuki, Toshinori Kouchi

Journal of Physics: Conference Series 2701 ( 1 ) 012056 - 012056 2024.2

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Publishing type：Research paper (scientific journal) Publisher：IOP Publishing

Abstract

This study aims to experimentally examine conditions that should be satisfied by a calibration position of a constant-temperature hot-wire anemometer. Specifically, this study addresses an appropriate measurement point when this calibration is performed downstream of a turbulent field generated by a multi-scale turbulence grid. The hot-wire measurement in this study is based on an I-type probe with a standard 5 μm tungsten wire. The hot-wire anemometer in this study is small and can be attached to a probe support. In this study, uncertainty in the calibration curve of the hot-wire measurement is first checked. Here, Pitot tube velocimetry to obtain the calibration curves is carried out using two bell-type micro-differential pressure gauges. Then, the characteristics of the obtained velocity fluctuations and turbulence will be examined. Based on this relative velocity fluctuation RMS value, the effects of the obtained streamwise velocity fluctuation on output voltage are obtained by asymptotically expanding a calibration curve. Using these results, the intensity of the free-stream turbulence, which has a negligible effect on output voltage giving a calibration curve, is clarified.

DOI： 10.1088/1742-6596/2701/1/012056

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Other Link： https://iopscience.iop.org/article/10.1088/1742-6596/2701/1/012056/pdf
LES analysis of local isotropic turbulence depending on the spatial scale of the external forcing field Reviewed

Koki Minami, Hiroki Suzuki, Toshinori Kouchi

Journal of Physics: Conference Series 2701 ( 1 ) 012055 - 012055 2024.2

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Publishing type：Research paper (scientific journal) Publisher：IOP Publishing

Abstract

The study investigates the effect of the parameterisation of an external force scheme based on trigonometric functions on turbulence. In particular, the dependence of the generated turbulence on the Reynolds number and the influence of its spatial parameters are investigated. The turbulence used is generated by a large-eddy simulation based on a high-precision finite volume method, and the turbulence energy and isotropy of the turbulence are also investigated. The parameter of the external force field used in this study characterises the wavelength of the trigonometric function, and the influence of this parameter on the spatial scale is studied in detail. As a result, steady turbulent fields are generated and isotropic turbulence is observed at different spatial scales of the external force field with M=2, 3 and 4. The property of increasing turbulence energy with increasing Reynolds number is confirmed.

DOI： 10.1088/1742-6596/2701/1/012055

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Other Link： https://iopscience.iop.org/article/10.1088/1742-6596/2701/1/012055/pdf
Locally Broken Shock Wave Detection with One-Dimensional Convolutional Neural Network in Shock Turbulence Interaction

Kento Tanaka, Toshinori Kouchi, Hiroki Suzuki, Koichi Takeuchi

AIAA SCITECH 2024 Forum 2024-2340 2024.1

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Language：English Publishing type：Research paper (international conference proceedings) Publisher：American Institute of Aeronautics and Astronautics

DOI： 10.2514/6.2024-2340

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Phase-lock Analysis of Two-Dimensional Transonic Shock Buffet by Using Machine Learning

Tsubasa Kikuchi, Toshinori Kouchi, Kento Tanaka, Koichi Takeuchi

AIAA SCITECH 2024 Forum 2024-0905 2024.1

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Authorship：Corresponding author Language：English Publishing type：Research paper (international conference proceedings) Publisher：American Institute of Aeronautics and Astronautics

DOI： 10.2514/6.2024-0905

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Assessing OpenFOAM-based Large-eddy Simulation Using Decay Characteristics of An Isotropic Taylor-green Vortex Reviewed

Akira Ono, Makoto Chitose, Hiroki Suzuki, Toshinori Kouchi

Journal of Physics: Conference Series 2694 ( 1 ) 012004 - 012004 2024.1

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Publishing type：Research paper (scientific journal) Publisher：IOP Publishing

Abstract

The aim of this study is to investigate OpenFOAM using isotropic TGV flows. The main focus is on the establishment of energy conservation laws, in particular using inviscid fields to assess energy constancy; Large-Eddy Simulation (LES) is applied and the results are compared with those obtained using spectral methods; unlike previous studies of OpenFOAM, this study uses an unsteady turbulent TGV flow. The computational methods used are a central difference method, a PISO algorithm and a Smagorinsky model. The study revealed errors in the conservation of kinetic energy in the OpenFOAM analysis. In particular, the energy decay was significant at high spatial resolution, confirming the different turbulence energy decay characteristics of DNS and OpenFOAM. However, when the model constant was 0.6, the decay characteristics were shown to be in good agreement with DNS.

DOI： 10.1088/1742-6596/2694/1/012004

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Other Link： https://iopscience.iop.org/article/10.1088/1742-6596/2694/1/012004/pdf
Comparative Testing the Uncertainty of A/D Converters in A Hot-Wire Anemometer Measurement Using Grid-Generated Turbulence Reviewed

Hiroto Yamaguchi, Hiroki Suzuki, Toshinori Kouchi

Journal of Physics: Conference Series 2694 ( 1 ) 012003 - 012003 2024.1

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Publishing type：Research paper (scientific journal) Publisher：IOP Publishing

Abstract

This study investigates the uncertainty of the A/D converter when measuring multi-scale turbulence fluctuations using a hot-wire anemometer. The flow is generated in a low-speed wind tunnel, the turbulence is generated by a turbulence grid and the fluctuations are measured. A compact hot-wire anemometer was used and a high accuracy A/D converter was introduced for the measurements. Methods to minimise the influence of noise were also incorporated and measurements were carried out in two situations, one with and one without turbulence. The experimental results showed that measurements under a specific condition (Case 1 in this study) had the sufficienty reproducibility of turbulence fluctuations and the least effect of noise. The results showed that the high frequency characteristics of the turbulence could also be accurately measured under this condition. In conclusion, it is clear that the choice of a suitable A/D converter and the optimisation of the measurement environment are critical for turbulence measurements with a hot-wire anemometer.

DOI： 10.1088/1742-6596/2694/1/012003

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Other Link： https://iopscience.iop.org/article/10.1088/1742-6596/2694/1/012003/pdf
Fundamental numerical analysis clarifying the response of incompressible turbulence fields to the uncertainty of kinetic energy conservation Reviewed

Makoto Chitose, Hiroki Suzuki, Kento Tanaka, Toshinori Kouchi

Proceedings of the International Conference on Power Engineering 2023 (ICOPE-2023) ICOPE-2023-1274 2023.5

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Language：English Publishing type：Research paper (international conference proceedings)

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Examination of multi-scale generated decaying turbulence validated for the influence of wind tunnel blockage Reviewed

Hiroto Yamaguchi, Hiroki Suzuki, Kento Tanaka, Toshinori Kouchi

Proceedings of the International Conference on Power Engineering 2023 (ICOPE-2023) ICOPE-2023-1268 2023.5

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Language：English Publishing type：Research paper (international conference proceedings)

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Dynamic Mode Decomposition of Simultaneous Dual-layer Focusing Schlieren and Unsteady Pressure-Sensitive Paint Measurements for Transonic Buffet on a Swept Wing

Shota Fukumoto, Toshinori Kouchi, Yosuke Sugioka, Shunsuke Koike

AIAA SCITECH 2023 Forum 2023-1180 2023.1

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Language：English Publishing type：Research paper (international conference proceedings) Publisher：American Institute of Aeronautics and Astronautics

DOI： 10.2514/6.2023-1180

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Experimental comparison of shock buffet on unswept and 10-deg swept wings Reviewed

Yosuke Sugioka, Toshinori Kouchi, Shunsuke Koike

EXPERIMENTS IN FLUIDS 63 ( 8 ) 2022.8

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Authorship：Corresponding author Language：English Publishing type：Research paper (scientific journal)

DOI： 10.1007/s00348-022-03482-x

Web of Science

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Impact of Pitot tube diameter on the centre line mean flow velocity in multi-scale grid-generated turbulence Reviewed

Hiroto Yamaguchi, Hiroki Suzuki, Kento Tanaka, Toshinori Kouchi

Journal of Physics: Conference Series 2313 ( 1 ) 012001 - 012001 2022.7

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Language：English Publishing type：Research paper (scientific journal) Publisher：IOP Publishing

Abstract

In this study, the impact of the leading-edge diameter of a Pitot tube on the mean flow of the decaying turbulence generated by a multi-scale grid was investigated. Standard Pitot tubes with leading edge diameters of 4 and 6 mm were used in this study, and a multi-scale grid was installed at the entrance of the test section to generate the decaying turbulence. The characteristic velocity was observed to be 2.8 m/s. In the downstream region of the test section, the mean velocities measured with the two Pitot tubes were in sufficiently good agreement, as well as the acceleration parameters calculated in this region. However, in the upstream region, the mean flow velocities obtained with the two Pitot tubes were slightly different. The thin Pitot tube showed a higher mean flow velocity in this region, corresponding to the jet-like structure that has been described in previous research. In contrast, this higher mean velocity in the upstream region was not observed in the mean flow velocity distribution obtained with the thick Pitot tube. This difference is discussed here from the perspective of the turbulent component and measurement uncertainty.

DOI： 10.1088/1742-6596/2313/1/012001

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Other Link： https://iopscience.iop.org/article/10.1088/1742-6596/2313/1/012001/pdf
Development of a single-scale initial flow field into steady homogeneous turbulence with validating a constructed Fourier spectral analysis Reviewed

Hiroki Suzuki, Toshinori Kouchi

Journal of Physics: Conference Series 2313 ( 1 ) 012008 - 012008 2022.7

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Publishing type：Research paper (scientific journal) Publisher：IOP Publishing

Abstract

This study presents the development of a single-scale initial velocity field into steady homogeneous isotropic turbulence. Here, we verify a constructed Fourier spectral analysis, which is then used to approach the present issue. The present homogeneous isotropic turbulence is maintained steady by using a linear forcing scheme of Lundgren (2003). Here, two values of the primary coefficient are set here for this scheme. The initial velocity field is also set to maintain the flow globally isotropic. Temporal developments of turbulence statistics, visualization results and structure functions are examined in this study. As shown in a previous study, Rosales and Meneveau (2005), the turbulence length scale at a steady-state could remain independent of a value used for the linear forcing coefficient. The turbulence fields needed 10 to 15 times longer than the turbulence time scale to achieve this steady-state. A larger amount of time was needed for the structure functions to reach their steady-state profiles than for the turbulence statistics.

DOI： 10.1088/1742-6596/2313/1/012008

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Other Link： https://iopscience.iop.org/article/10.1088/1742-6596/2313/1/012008/pdf
Side-Wall Effects on the Global Stability of Swept and Unswept Supercritical Wings at Buffet Conditions

Andrea Sansica, Atsushi Hashimoto, Shunsuke Koike, Toshinori Kouchi

AIAA SCITECH 2022 Forum 2022.1

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Authorship：Last author Publishing type：Research paper (international conference proceedings) Publisher：American Institute of Aeronautics and Astronautics

DOI： 10.2514/6.2022-1972

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Extracting Principal Modes of Two-dimensional Shock Buffet by Using Dynamic Mode Decomposition Reviewed

Fukumoto Shota, Kouchi Toshinori, Otera Kengo, Sugioka Yosuke

JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 70 ( 3 ) 82 - 92 2022

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Authorship：Corresponding author Language：Japanese Publisher：THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

Self-oscillation of a shock wave, which is called a transonic shock buffet, occurs on a wing surface in a transonic flow. Lee and Crouch explained the self-sustained mechanism by different pressure wave propagations but there is no experimental evidence of which feedback loop is dominant. The principal aim of the present study is to identify the dominant feedback path of pressure waves related to the shock buffet using high-speed focusing schlieren movies. The experimental data showed that the flow fields include complicated phenomena such as a lot of pressure waves with a broad range of frequency. Therefore, we performed dynamic mode decomposition (DMD) analysis to extract dominant phenomena for the buffet. DMD modes whose frequencies corresponded to the shock oscillation frequencies were extracted and investigated. DMD modes revealed that pressure perturbations generated at the shock foot and the perturbation propagated to the height-wise direction along with the shock wave. This feedback pass is similar to that observed by Crouch using the global stability analysis for NACA 0012 airfoil.

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Existence of dual solutions and three-dimensional instability in helical pipe flow Reviewed

Anup Kumer Datta, Toshinori Kouchi, Yasutaka Hayamizu, Yasunori Nagata, Kyoji Yamamoto, Shinichiro Yanase

Chinese Journal of Physics 73 154 - 166 2021.10

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DOI： 10.1016/j.cjph.2021.07.002

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Sea-Level Static Tests of Rocket–Ramjet Combined Cycle Engine Model Reviewed

Sadatake Tomioka, Masao Takegoshi, Toshinori Kochi, Kanenori Kato, Toshihito Saito, Kouichiro Tani

Journal of Propulsion and Power 37 ( 3 ) 381 - 390 2021.5

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Influence of Partial Electrical Conducting Wall on Electrodynamic Flow Control Reviewed

NAGATA Yasunori, YAMANE Eisuke, NORII Takumi, KOUCHI Toshinori, YANASE Shinichiro

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 19 ( 1 ) 68 - 74 2021

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The electrodynamic flow control effect using an applied magnetic field has a potential of innovative technology for aerodynamic force control of atmospheric entry vehicle because of no requirement of mechanical devices. To control this effect and aerodynamic force, we proposed a new approach using exposed electrodes on the vehicle surface. If the induced electric current is bypassed via exposed electrodes, the electromagnetic field could be changed. In this study, the influence of the partial electrical conducting wall, which is consisted of insulating and conducting walls, is numerically investigated. As a result of the MHD simulation, flow field could be changed by the vehicle surface condition. Especially, in the frontal region of the vehicle where strong Lorentz force acts, if the conducting wall is installed to electrically short to the shoulder position, the electric field within this region and the electrodynamic effect is significantly changed. Additionally, stepwise drag variation could be made by selectable shorted electrodes.

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Transverse Jet Mixing in a Supersonic Grid Turbulence

Toshinori Kouchi, Masaki Iwachido, Takahiro Nakagawa, Yasunori Nagata, Shinichiro Yanase

AIAA Scitech 2020 Forum 35th 2020.1

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DOI： 10.2514/6.2020-2040

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LES Analysis of Transverse Jet Mixing in Supersonic Free-stream Turbulence

Yasunori Nagata, Seitaro Yokoi, Rei Aoki, Toshinori Kouchi, Shinichiro Yanase

AIAA Scitech 2020 Forum 2020.1

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DOI： 10.2514/6.2020-1335

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Numerical Study of the Lift Force, Velocities and Pressure Distribution of a Single Air Bubble and Two Interacting Air Bubbles Rising in Quiescent Liquid Reviewed

Chao Guan, Shinichiro Yanase, Koji Matsuura, Toshinori Kouchi, Yasunori Nagata

Open Journal of Fluid Dynamics 10 ( 01 ) 31 - 51 2020

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DOI： 10.4236/ojfd.2020.101003

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Numerical study of air-entraining and submerged vortices in a pump sump Reviewed

Shinichiro Yanase, Ryo Yamasaki, Toshinori Kouchi, Shunsuke Hosoda, Yasunori Nagata, Higuchi Shunji, Toshihiko Kawabe, Toshihiro Takami

IOP Conference Series: Earth and Environmental Science 240 ( 3 ) 032001 - 032001 2019.3

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DOI： 10.1088/1755-1315/240/3/032001

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Hydrodynamic instability with convective heat transfer through a curved channel with strong rotational speed

Mohammad Sanjeed Hasan, Rabindra Nath Mondal, Toshinori Kouchi, Shinichiro Yanase

AIP Conference Proceedings 2121 2019

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DOI： 10.1063/1.5115851

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Acetone-condensation nano-particle image velocimetry in a supersonic boundary layer

Toshinori Kouchi, Seiya Fukuda, Syouma Miyai, Yasunori Nagata, Shinichiro Yanase

AIAA Scitech 2019 Forum AIAA 2019-1821 2019

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DOI： 10.2514/6.2019-1821

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Extension of VSL Method for Electrodynamic Heat Shield Analysis Reviewed

Nagata Yasunori, Ishihara Ryoichi, Maeda Shingo, Kouchi Toshinori, Yanase Shinichiro

JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 67 ( 1 ) 16 - 24 2019

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The electrodynamic heat shield is new type of heat protection system for atmospheric-entry vehicle, which utilizes the Lorentz force acting on the weakly ionized plasma flow inside the shock layer. A huge amount of calculation is necessary to estimate overall effect of the electrodynamic heat shield, because its effect interacts with the atmospheric-entry trajectory. In the present study, the Viscous Shock Layer (VSL) analysis method for electrodynamic heat shield is proposed for the quick analysis, which can calculate much faster than Navier-Stokes (NS) simulation. For this purpose, the VSL equations for the electrodynamic heat shield analysis are introduced under the ideal gas assumption, including circumferential momentum equation and Maxwell equations. The new method is also proposed to solve the new VSL equations. By the comparison to the NS simulation, the new VSL method gives good estimations of drag force and wall heat flux for wide ranges of interaction parameter and Hall parameter although the slight difference of wall heat flux at the stagnation point is observed. Therefore, the present VSL method could be applicable to the estimation tool of the electrodynamic heat shield effect. 

DOI： 10.2322/jjsass.67.16

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CFD Simulation of an Ejector-jet Engine Reviewed

Hiromu Inoue, Toshinori Kouchi, Yasunori Nagata, Shinichiro Yanase

Asia-pacific International Symposium on Aerospace Technology 2019 APISAT-733 2019

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Numerical Study on Motion of a Single Spherical Bubble near Vertical Wall in the quiescent fluid using the Modified Force-coupling Method Reviewed

GUAN Chao, 柳瀬眞一郎, 松浦宏治, 河内俊憲, 永田靖典

ながれ 37 ( 3 ) 281 - 289 2018.6

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LES Investigation of Supersonic Mixing Layer Using Different Type of Gas

Tatsuya Kishi, Toshinori Kouchi, Yasunori Nagata, Shinichiro Yanase

Asian Joint Conference on Propulsion and Power 2018 AJCPP2018-035 2018

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Laminar forced convective heat transfer in helical pipe flow Reviewed

Anup Kumer Datta, Shinichiro Yanase, Toshinori Kouchi, Mohammed M.E. Shatat

International Journal of Thermal Sciences 120 41 - 49 2017.10

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DOI： 10.1016/j.ijthermalsci.2017.05.026

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Numerical Study of Turbulent Helical Pipe Flow With Comparison to the Experimental Results Reviewed

Anup Kumer Datta, Yasutaka Hayamizu, Toshinori Kouchi, Yasunori Nagata, Kyoji Yamamoto, Shinichiro Yanase

Journal of Fluids Engineering 139 ( 9 ) 2017.9

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DOI： 10.1115/1.4036477

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Extracting dominant turbulent structures in supersonic flow using two-dimensional Fourier transform Reviewed

Toshinori Kouchi, Goro Masuya, Shinichiro Yanase

Experiments in Fluids 58 ( 8 ) 2017.8

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DOI： 10.1007/s00348-017-2377-z

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Effect of Torsion on the Friction Factor of Helical Pipe Flow Reviewed

Anup Kumer Datta, Shinichiro Yanase, Yasutaka Hayamizu, Toshinori Kouchi, Yasunori Nagata, Kyoji Yamamoto

Journal of the Physical Society of Japan 86 ( 6 ) 064403 - 064403 2017.6

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DOI： 10.7566/jpsj.86.064403

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Modified Lee’s Transonic Buffet Mechanism Inspired with Fast-framing Focusing-schlieren Visualization

Toshinori Kouchi, Shingo Yamaguchi, Yuki Yamashita, Shinichiro Yanase, Shunsuke Koike

55th AIAA Aerospace Sciences Meeting 2017.1

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DOI： 10.2514/6.2017-0265

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OpenFOAM analysis of air-entraining and submerged vortices in pump sump Reviewed

YAMASAKI Ryo, KOUCHI Toshinori, NAGATA Yasunori, YANASE Shinichiro

Transactions of the JSME (in Japanese) 83 ( 853 ) 17 - 00181-17-00181 2017

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Language：Japanese Publisher：The Japan Society of Mechanical Engineers

Numerical prediction of air-entraining and submerged vortices in pump sumps is important for engineering applications. The validation of pump sump simulations, however, still is not enough, because the simulations is very complicated; for examples, treatment of gas-liquid interface, detection method of the vortices and selection of turbulence model etc. We conducted numerical simulations of the benchmark experiments of the pump sump conducted by Matsui et al. (2006, 2016) and compared the simulation with the experimental data to investigate the effects of turbulence model, grid density and detection method of the vortices. We determined a threshold of the gas-liquid fraction function of VOF method (α) and the second invariant of velocity gradient tensor (Q₂) to detect the air-entraining and submerged vortices by using vorticity, respectively. This method well detected the vortices and well reproduced the experiments for the RANS simulation using SST k-ω model. Large eddy simulation using Smagorinsky model, however, was sensitive to the grid system and difficult to reproduce the experimental vortex structures even for the finest grid system having 3.7 million cells.

DOI： 10.1299/transjsme.17-00181

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Supersonic Combustion using Multiple Stinger-shaped Injectors Reviewed

Toshinori KOUCHI, Sadatake TOMIOKA, Kohshi HIRANO, Akiko MATSUO, Goro MASUYA

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 60 ( 1 ) 56 - 59 2017

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DOI： 10.2322/tjsass.60.56

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Large-scale vortical structure detection using microphone array in a semiconductor single wafer spin cleaner Reviewed

Toshinori KOUCHI, Yuki MIYOSHI, Yusuke NAKANO, Yasunori NAGATA, Shinichiro YANASE

Transactions of the JSME (in Japanese) 83 ( 845 ) 16 - 00441 2017

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DOI： 10.1299/transjsme.16-00441

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Application of the Modified Force-Coupling Method of Tracing the Trajectories of Spherical Bubbles with Solid-Like and Slip Surfaces Reviewed

Chao Guan, Shinichiro Yanase, Koji Matsuura, Toshinori Kouchi, Yasunori Nagata

Open Journal of Fluid Dynamics 07 ( 04 ) 657 - 672 2017

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DOI： 10.4236/ojfd.2017.74043

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Optimization of Focusing Schlieren System for an Axisymmetric Ejector Reviewed

Masato Nakaya, Toshinori Kouchi, Yasunori Nagata, Shinichiro Yanase

11th Pacific Symposium on Flow Visualization and Image Processing PSFVIP11-055 2017

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Combined Fast-framing Schlieren Imaging and Stereo PIV Measurements in a Supersonic Boundary-layer Reviewed

Mayu Mizoguchi, Kazuki Yamauchi, Toshinori Kouchi, Yasunori Nagata, Shinichiro Yanase

9th JSME-KSME Thermal and Fluids Engineering Conference TFEC9-1463 2017

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Wavelet analysis of transonic buffet on a two-dimensional airfoil with vortex generators Reviewed

Toshinori Kouchi, Shingo Yamaguchi, Shunske Koike, Tsutomu Nakajima, Mamoru Sato, Hiroshi Kanda, Shinichiro Yanase

Experiments in Fluids 57 ( 11 ) 2016.11

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DOI： 10.1007/s00348-016-2261-2

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Wavelet Analysis of Unsteady Shock-wave Motion on Two-dimensional Airfoil with Vortex Generators

Toshinori Kouchi, Shingo Yamaguchi, Shunsuke Koike, Shinichiro Yanase, Tsutomu Nakajima, Mamoru Sato, Atsushi Kanda

54th AIAA Aerospace Sciences Meeting 2016.1

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DOI： 10.2514/6.2016-1766

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Turbulent diffusion flux of transverse jet into pseudo-shock wave

Taekjin Lee, Toshinori Kouchi, Yoshinori Oka, Goro Masuya

54th AIAA Aerospace Sciences Meeting AIAA 2016-0662 2016

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DOI： 10.2514/6.2016-0662

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Development of DEM–CFD Simulation of Combustion Flow in Incinerator with the Representative Particle Model Reviewed

Kenya Kuwagi, Toshihiro Takami, Azri Bin Alias, Degang Rong, Hiroshi Takeda, Shinichiro Yanase, Toshinori Kouchi, Toru Hyakutake, Kaoru Yokoyama, Yoshiyuki Ohara, Nobuo Takahashi, Noritake Sugitsue

Journal of Chemical Engineering of Japan 49 ( 5 ) 425 - 434 2016

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DOI： 10.1252/jcej.15we099

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Effects of Upstream Disturbances on Supersonic Flowfield with Transverse Injection Reviewed

Shohei URAMOTO, Toshinori KOUCHI, Goro MASUYA

JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 64 ( 4 ) 244 - 252 2016

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DOI： 10.2322/jjsass.64.244

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Focusing-schlieren visualization in a dual-mode scramjet Reviewed

Toshinori Kouchi, Christopher P. Goyne, Robert D. Rockwell, James C. McDaniel

Experiments in Fluids 56 ( 12 ) 2015.12

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DOI： 10.1007/s00348-015-2081-9

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Fast-framing Focusing Schlieren Visualization of Two-dimensional Wing Buffet Reviewed

YAMAGUCHI Shingo, KOUCHI Toshinori, KOIKE Shunsuke, NAKAJIMA Tsutomu, SATO Mamoru, KANDA Hiroshi, YANASE Shinichiro

JOURNAL OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES 63 ( 4 ) 166 - 174 2015

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We visualized two-dimensional wing buffet using fast-framing focusing schlieren method. A supercritical airfoil of NASA SC(2)-0518 was used in this study. Mach number of the freestream was 0.7, and Reynolds number based on the wing code (c) was 5×10⁶. Angle of attack without corrections (α) was changed from 4° to 6°. The present focusing schlieren system had ±18mm depth of field, which was narrow than spanwise region where the two-dimensionality of the flow field was maintained. 8,345 successive images were captured by high speed CMOS camera with 7,000 frames per second with 20μs exposure time. The present imaging system well captured the shock wave motion on the airfoil. At α = 4°, the shock wave was positioned at x/c&sim;0.45. The shock wave was slightly fluctuated with a frequency of 585.5Hz. Above α = 5°, the wing buffet occurred. The buffet frequency increased as increasing α. The focusing schlieren movies revealed that the shock wave was bifurcated on the wing surface, as the shock traveling upstream. The boundary layer largely separated from the leading oblique foot of the bifurcated shock wave, whereas, the bifurcated shock wave changed into a normal shock and the flow separation disappeared, as the shock traveling downstream. For both cases, many pressure waves propagated from the downstream of the shock wave to the upstream. These waves merged with the shock wave, and seem to drive the shock oscillation.

DOI： 10.2322/jjsass.63.166

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Periodical structure of vortices in a semiconductor single wafer spin cleaner Reviewed

Toshinori KOUCHI, Naoya FUKUDA, Yusuke NAKANO, Yoshiya SHIMIZU, Yasunori NAGATA, Shinichiro YANASE

Transactions of the JSME (in Japanese) 81 ( 829 ) 15 - 00273 2015

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DOI： 10.1299/transjsme.15-00273

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Collaborative Experimental and Computational Study of a Dual-Mode Scramjet Combustor Reviewed

Rockwell, Robert D., Jr., Goyne, Christopher R., Rice, Brian E., Kouchi, Toshinori, McDaniel, James C., Edwards, Jack R.

Journal of Propulsion and Power 30 ( 3 ) 530 - 538 2014.5

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DOI： 10.2514/1.B35021

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Combined Stereo-PIV and PLIF Measurements of Transverse Injection in Mach 2 Supersonic Flow Reviewed

Toshinori KOUCHI, Yoshinori OKA, Goro MASUYA, Shinichiro YANASE

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, AEROSPACE TECHNOLOGY JAPAN 12 ( APISAT-2013 ) a85 - a92 2014

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DOI： 10.2322/tastj.12.a85

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PIV measurement of vortical structures in a model of semiconductor single wafer cleaner Reviewed

Yoshiya SHIMIZU, Shinichiro YANASE, Toshinori KOUCHI, Yohei MORI, Naoya FUKUDA

Transactions of the JSME (in Japanese) 80 ( 815 ) FE0197 - FE0197 2014

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DOI： 10.1299/transjsme.2014fe0197

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Characteristics of Hydrogen Jets in Supersonic Crossflow: Large-Eddy Simulation Study Reviewed

Watanabe, Junya, Kouchi, Toshinori, Takita, Kenichi, Masuya, Goro

Journal of Propulsion and Power 29 ( 3 ) 661 - 674 2013.5

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DOI： 10.2514/1.B34521

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Supersonic Combustion Using a Stinger-Shaped Fuel Injector Reviewed

Kouchi, Toshinori, Masuya, Goro, Hirano, Kohshi, Matsuo, Akiko, Tomioka, Sadatake

Journal of Propulsion and Power 29 ( 3 ) 639 - 647 2013.5

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DOI： 10.2514/1.B34524

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Large-Eddy Simulation of Jet in Supersonic Crossflow with Different Injectant Species Reviewed

Junya Watanabe, Toshinori Kouchi, Kenichi Takita, Goro Masuya

AIAA JOURNAL 50 ( 12 ) 2765 - 2778 2012.12

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DOI： 10.2514/1.J051550

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Flowfield characteristics of a transverse jet into supersonic flow with pseudo-shock wave Reviewed

H. Yamauchi, B. Choi, K. Takae, T. Kouchi, G. Masuya

Shock Waves 22 ( 6 ) 533 - 545 2012.11

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DOI： 10.1007/s00193-012-0384-9

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Turbulent Characteristics for Jet Injected into Supersonic Flow with Pseudo Shock Wave Reviewed

Byugil Choi, Koichi Takae, Toshinori Kouchi, Goro Masuya

JOURNAL OF PROPULSION AND POWER 28 ( 5 ) 971 - 981 2012.9

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DOI： 10.2514/1.B34371

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Flowfield Characteristics of a Hypermixer Interacting with Transverse Injection in Supersonic Flow Reviewed

Chae-Hyoung Kim, In-Seuck Jeung, Byungil Choi, Toshinori Kouchi, Goro Masuya

AIAA JOURNAL 50 ( 8 ) 1742 - 1753 2012.8

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DOI： 10.2514/1.J051588

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Mechanism and Control of Combustion-Mode Transition in a Scramjet Engine Reviewed

Kouchi, Toshinori, Masuya, Goro, Mitani, Tohru, Tomioka, Sadatake

Journal of Propulsion and Power 28 ( 1 ) 106 - 112 2012.1

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DOI： 10.2514/1.B34172

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Quasi-one dimensional modeling on vitiation effects for a dual-mode combustor

Junji Noda, Masaki Ohkoshi, Toshinori Kouchi, Goro Masuya, Sadatake Tomioka, Robert D. Rockwell, Christopher P. Goyne

18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012 ( 2012-5862 ) 2012

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DOI： 10.2514/6.2012-5862

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Quantification of convection velocity and dominant scale of large-scale structures by high-speed schlieren imaging

Toshinori Kouchi, Goro Masuya

48th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2012 AIAA 2012-4148 2012

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DOI： 10.2514/6.2012-4148

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Focusing-schlieren visualization in direct-connect dual-mode scramjet

Toshinori Kouchi, Christopher P. Goyne, Robert D. Rockwell, Roger Reynolds, Roland Krauss, James C. McDaniel

18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012 2012

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DOI： 10.2514/6.2012-5834

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Large-eddy /reynolds-averaged navier-stokes simulations of a dual-mode scramjet combustor

Jesse A. Fulton, Jack R. Edwards, Hassan A. Hassan, Robert Rockwell, Christopher Goyne, Jim McDaniel, Chad Smith, Andrew Cutler, Craig Johansen, Paul M. Danehy, Toshinori Kouchi

50th AIAA Aerospace Sciences Meeting Including the New Horizons Forum and Aerospace Exposition 2012

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Effect of vent mixer to mixing characteristics in supersonic flow

Chae Hyoung Kim, In Seuck Jeung, Byungil Choi, Toshinori Kouchi, Goro Masuya

28th Congress of the International Council of the Aeronautical Sciences 2012, ICAS 2012 4 2864 - 2872 2012

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Large-eddy simulation of pseudo-shock wave in a square duct

S. Lee, J. Watanabe, T. Kouchi, K. Takita, G. Masuya

18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012 2012

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Velocity field in secondary combustor of ejector-jet

Kiyoshi Nojima, Toshinori Kouchi, Goro Masuya, Sadatake Tomioka

18th AIAA/3AF International Space Planes and Hypersonic Systems and Technologies Conference 2012 ( 2012-5838 ) 2012

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DOI： 10.2514/6.2012-5838

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Turbulent Structure of Supersonic Flowfield Reviewed

Shohei Uramoto, Toshinori Kouchi, Goro Masuya

Journal of Fluid Science and Technology 7 ( 2 ) 231 - 241 2012

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Language：English Publishing type：Research paper (scientific journal) Publisher：The Japan Society of Mechanical Engineers

We investigated a supersonic flowfield with transverse injection of air or helium by stereoscopic particle image velocimetry and calculated single-time two-point spatial correlations of velocity fluctuations. For both injection gases, the bow shock wave formed by the injection and its reflection from the upper wall could be seen in the mean velocity distribution. In the velocity fluctuation intensity distribution, we observed vibrating counter-rotating vortex pair and the Reynolds stress was formed along the track of the maximum mean velocity gradient. Correlations showed the scale structure of turbulence and the shapes of the correlation region changed with the selected velocity component. Differences were observed between the results obtained for the two injectant species.

DOI： 10.1299/jfst.7.231

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Characteristic Study on Effect of the Vent Mixer to Supersonic Fuel-Air Mixing with Stereoscopic-PIV Method

Kim, Chae-Hyoung, SEUCK, JEUNG IN, Kouchi, Toshinori, Masuya, Goro

2012

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DOI： 10.6108/KSPE.2012.16.4.050

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Turbulence Induced by Transverse Injection and Pseudo-Shock Wave in Supersonic Flow

Goro Masuya, Byung-Il Choi, Koichi Takae, Toshinori Kouchi

20th International Symposium on Air Breathing Engines ( ISABE Paper 2011-1525 ) 2011.9

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Numerical Study on the Turbulent Structure of Transverse Jet into Supersonic Flow Reviewed

Junya Watanabe, Toshinori Kouchi, Kenichi Takita, Goro Masuya

AIAA JOURNAL 49 ( 9 ) 2057 - 2067 2011.9

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DOI： 10.2514/1.J051067

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Mixing Characteristics of Secondary Fuel in RBCC Ejector-Jet Mode Operation

Kiyoshi Nojima, Toshinori Kouchi, Goro Masuya, Sadatake Tomioka

28th International Symposium on Space Technology and Science ( ISTS 2011-a-65 ) 2011.6

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Correlation between Hypermixer and Fuel Injection Locations

Chae-hyoung Kim, In-Seuck Jeung, Byungil Choi, Toshinori Kouchi, Goro Masuya

17th AIAA International Space Planes and Hypersonic Systems and Technologies Conference 2011.4

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DOI： 10.2514/6.2011-2343

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Effect of fuel injection location on a plasma jet assisted combustion with a backward-facing step Reviewed

Kim, Chae-Hyoung, Jeung, In-Seuck, Choi, Byungil, Kouchi, Toshinori, Takita, Kenichi, Masuya, Goro

Proceedings of the Combustion Institute 33 ( 2 ) 2375 - 2382 2011.1

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DOI： 10.1016/j.proci.2010.07.057

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Effect of fuel injection locations with a hyper mixer in supersonic combustion

Chae Hyoung Kim, In Seuck Jeung, Byungil Choi, Toshinori Kouchi, Goro Masuya

47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2011 ( 2011-5830 ) 2011

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DOI： 10.2514/6.2011-5830

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Large-eddy simulations of hydrogen and ethylene injections into a supersonic crossflow

Junya Watanabe, Toshinori Kouchi, Kenichi Takita, Goro Masuya

47th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2011 ( 2011-5764 ) 2011

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DOI： 10.2514/6.2011-5764

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Flowfield characteristics on a vent slot mixer in supersonic flow Reviewed

Kim, C., Sung, K., Jeung, I. -S., Choi, B., Kouchi, T., Masuya, G.

Shock Waves 20 ( 6 ) 559 - 569 2010.12

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DOI： 10.1007/s00193-010-0280-0

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Other Link： http://link.springer.com/article/10.1007/s00193-010-0280-0/fulltext.html
Effect of a Vent Slot Mixer with a Plasma Jet Torch in Unheated Supersonic Flow

Chae-hyoung Kim, In-seuck Jeung, Byungil Choi, Toshinori Kouchi, Goro Masuya

46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 2010.7

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Publishing type：Research paper (international conference proceedings) Publisher：American Institute of Aeronautics and Astronautics

DOI： 10.2514/6.2010-6644

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Penetration Characteristics of Pulsed Injection into Supersonic Crossflow

Toshinori Kouchi, Keita Sasaya, Junya Watanabe, Hiroharu Shibayama, Goro Masuya

46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 2010.7

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DOI： 10.2514/6.2010-6645

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Scalar spatial correlations in a supersonic mixing flowfield Reviewed

Hidemi Takahashi, Hiroki Oso, Toshinori Kouchi, Goro Masuya, Mitsutomo Hirota

AIAA Journal 48 ( 2 ) 443 - 452 2010.2

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DOI： 10.2514/1.44684

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Development of a New Supersonic Mixier for Dual-Mode Scramjet Engine Combustor

Chae-hyoung Kim, In-Seuck Jeung, Byungil Choi, Toshinori Kouchi, Goro Masuya

16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference 2009.10

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DOI： 10.2514/6.2009-7257

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Time-Space Trajectory of Unsteady Jet into Supersonic Crossflow Using High-Speed Framing Schlieren Images

Toshinori Kouchi, Takahisa Hoshino, Keita Sasaya, Goro Masuya

16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference 2009.10

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Publishing type：Research paper (international conference proceedings) Publisher：American Institute of Aeronautics and Astronautics

DOI： 10.2514/6.2009-7316

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Mechanism of Mixing Enhanced by Pseudo-Shock Wave

Hideki Yamauchi, Byongil Choi, Toshinori Kouchi, Goro Masuya

47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace Exposition 2009.1

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Publishing type：Research paper (international conference proceedings) Publisher：American Institute of Aeronautics and Astronautics

DOI： 10.2514/6.2009-25

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Supersonic combustion with supersonic injection through diamond-shaped orifices Reviewed

S. Tomioka, T. Kohchi, R. Masumoto, M. Izumikawa, A. Matsuo

45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 27 ( 6 ) 1196 - 1203 2009

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DOI： 10.2514/1.B34164

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Performance of a scramjet engine model in Mach 6 flight condition Reviewed

S. Ueda, T. Kouchi, M. Takegoshi, S. Tomioka, K. Tani

Shock Waves 1129 - 1134 2009

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Language：English Publishing type：Part of collection (book)

DOI： 10.1007/978-3-540-85181-3_54

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Design and Experimental Verification of Two Dimensional Asymmetric Supersonic Nozzle Reviewed

김채형, Masuya, Goro, 성근민, 최병일, Kouchi, Toshinori

Journal of the Korean Society for Aeronautical and Space Sciences 37 ( 9 ) 2009

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Aerodynamic Experiments of Small Scale Combined Cycle Engine in Various Mach Numbers Reviewed

Kouichiro TANI, Toshinori KOUCHI, Kanenori KATO, Noboru SAKURANAKA, Syuuichi WATANABE

TRANSACTIONS OF THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES, SPACE TECHNOLOGY JAPAN 7 ( ists26 ) Pa_59 - Pa_64 2009

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A small model aerodynamic tests of the combined cycle engine were carried out to evaluate its performance in subsonic and supersonic conditions. In this regime of the flow speed, the combined cycle engine operates as an ejector-jet or ramjet. The nitrogen gas was exhausted as the substitution for the actual rocket gas. In a subsonic condition, there appeared local pressure rise at the kink point of the ramp, increasing the pressure drag. Both wall pressure and the pitot pressure distribution at the exit of the model suggested that the flow structure is "two-layered" ; one is subsonic induced air flow, and the other is the supersonic rocket exhaust. A slit was carved on the topwall inside the isolator section, expecting a better suction performance in the ejector-jet mode. The modification actually had an effect to enhance the lower limit of the rocket pressure at which the choking of the induced air is achieved.

DOI： 10.2322/tstj.7.pa_59

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Combustion Performance of Supersonic Combustor with Stinger-Shaped Fuel Injector

Toshinori Kouchi, Kohshi Hirano, Kan Kobayashi, Sadatake Tomioka, Muneo Izumikawa, Akiko Matsuo

44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 2008.7

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DOI： 10.2514/6.2008-4503

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Matched pressure injections into a supersonic crossflow through diamond-shaped orifices Reviewed

Tomioka, Sadatake, Izumikawa, Muneo, Kouchi, Toshinori, Masuya, Goro, Hirano, Kohshi, Matsuo, Akiko

Journal of Propulsion and Power 24 ( 3 ) 471 - 478 2008.5

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DOI： 10.2514/1.35177

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Pumping Performance of RBCC Engine under Sea Level Static Condition 2nd Report: Two-Stream Flow Analysis of Ejector and Improvement of Pumping Performance Reviewed

河内俊憲, 河内俊憲, 富岡定毅, 苅田丈士

日本航空宇宙学会論文集 56 ( 651 ) 163 - 168 2008

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DOI： 10.2322/jjsass.56.163

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Pumping Performance or RBCC Engine under Sea Level Static Condition 1st Report: Numerical Prediction of Pumping Performance Reviewed

河内俊憲, 河内俊憲, 富岡定毅, 苅田丈士

日本航空宇宙学会論文集 56 ( 650 ) 110 - 115 2008

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DOI： 10.2322/jjsass.56.110

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New Injector Geometry for Penetration Enhancement of Perpendicular Jet into Supersonic Flow

Kohshi Hirano, Akiko Matsuo, Toshinori Kouchi, Muneo Izumikawa, Sadatake Tomioka

43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 2007.7

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DOI： 10.2514/6.2007-5028

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Pulsed Transverse Injection Applied to a Supersonic Flow

Toshinori Kouchi, Noboru Sakuranaka, Muneo Izumikawa, Sadatake Tomioka

43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 2007.7

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Publishing type：Research paper (international conference proceedings) Publisher：American Institute of Aeronautics and Astronautics

DOI： 10.2514/6.2007-5405

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エンジン風洞における超音速流の閉塞 Reviewed

三谷徹, 宮島博, 谷香一郎, 河内俊憲, 櫻中登, 渡邊修一

日本航空宇宙学会論文集 55 ( 636 ) 43 - 50 2007

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Language：Japanese

DOI： 10.2322/jjsass.55.43

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Performance of a RBCC Combustor Operating in Ramjet Mode

Toshinori Kouchi, Kan Kobayashi, Kenji Kudo, Atsuo Murakami, Kanenori Kato, Tomioka Sadatake

42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 2006.7

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Publishing type：Research paper (international conference proceedings) Publisher：American Institute of Aeronautics and Astronautics

DOI： 10.2514/6.2006-4867

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Evaluation of heat-flux on scramjet engine wall in Mach 6 flight condition

Shuichi Ueda, Masao Takegoshi, Toshinori Kouchi, Fumiei Ono, Toshihito Saito, Muneo Izumikawa

AIAA 57th International Astronautical Congress, IAC 2006 9 6344 - 6353 2006

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DOI： 10.2514/6.iac-06-c4.5.04

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Transition of Combustion Modes in a Scramjet Engine Reviewed

Kouchi, T, Mitani, T, Tomioka, S, Ueda, S

Proceedings of the 25th International Symposium on Space Technology and Science 107 - 114 2006

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Performance Comparison of Combined Fuel Injection Methods in a Staged-Combustion Scramjet Engine Reviewed

Ueda, S, Tomioka, S, Kouchi, T, Kobayashi, K, Kudo, K, Kato, K

Proceedings of the 25th International Symposium on Space Technology and Science 121 - 126 2006

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Flame structures and combustion efficiency computed for a Mach 6 scramjet engine Reviewed

Mitani, T, Kouchi, T

Combustion and Flame 142 ( 3 ) 187 - 196 2005.8

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DOI： 10.1016/j.combustflame.2004.10.004

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Numerical simulations in scramjet combustion with boundary-layer bleeding Reviewed

Kouchi, T, Mitani, T, Masuya, G

Journal of Propulsion and Power 21 ( 4 ) 642 - 649 2005.7

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DOI： 10.2514/1.7967

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Problems of Numerical Diffusion Found in Scramjets

Toshinori Kouchi, Tohru Mitani, Goro Masuya

AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference 2005.5

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Publishing type：Research paper (international conference proceedings) Publisher：American Institute of Aeronautics and Astronautics

DOI： 10.2514/6.2005-3216

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Heat Flux Prediction for Scramjet Engines, - Accuracy of Reynolds Analogy on Scramjet Internal Walls Reviewed

Kouchi, T, Mitani, T, Hiraiwa, T, Kodera, M, Masuya, G

Proceedings of the 24th International Symposium on Space Technology and Science 20 - 26 2004

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Scramjet Engine Performance Attained in RJTF Testing Reviewed

三谷徹, 富岡定毅, 苅田丈士, 谷香一郎, 鎮西信夫, 河内俊憲

日本航空宇宙学会論文集 52 ( 600 ) 1 - 9 2004

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DOI： 10.2322/jjsass.52.1

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Numerical Experiments of Scramjet Combustion with Boundary-Layer Bleeding

Toshinori Kouchi, Tohru Mitani, Masatoshi Kodera, Goro Masuya

12th AIAA International Space Planes and Hypersonic Systems and Technologies 2003.12

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Publishing type：Research paper (international conference proceedings) Publisher：American Institute of Aeronautics and Astronautics

DOI： 10.2514/6.2003-7038

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抗力測定によるスクラムジェットの推力性能見積り Reviewed

河内俊憲, 三谷徹, 平岩徹夫, 富岡定毅, 升谷五郎

日本航空宇宙学会論文集 51 ( 595 ) 403 - 411 2003

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DOI： 10.2322/jjsass.51.403

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Effects of Reynolds Number on Scramjet Inlet Performance Reviewed

Kouchi, T, Mitani, T, Kodera, M, Masuya, G

Proceedings of the 23rd International Symposium on Space Technology and Science 21 2412 - 2417 2002

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Books

工学のための物理数学

田村, 篤敬, 柳瀬, 真一郎, 河内, 俊憲

朝倉書店 2019.10 （ ISBN:9784254201680 ）

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Total pages：iv, 193p Language：Japanese

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MISC

高レイノルズ数空力を支える流体計測とデータ駆動型解析の試み Invited

河内俊憲

第488回航空懇談会 2023.9

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航空機の設計・開発を支える先進流体計測とデータ駆動型解析 Invited

河内俊憲

2022年度日本冷凍空調学会年次大会 2022.9

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Mean Velocity Measurements of Turbulent Boundary Layer at Re_θ=14,000 Developed on a Supersonic Wind Tunnel Wall

貝原涼弥, 黒瀬章弘, 河内俊憲

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) JAXA-SP-21-008 141 - 147 2022.2

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Dynamic Mode Decomposition of Simultaneous Dual-layer Focusing Schlieren and Unsteady Pressure-Sensitive Paint Measurements for Transonic Buffet on a Swept Wing

福本翔太, 河内俊憲, 杉岡洋介, 小池俊輔

飛行機シンポジウム講演集(CD-ROM) 60th 2022

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Spherical shock wave surface due to interference with uniform isotropic turbulence Evaluation of distortion

渡邉大成, 田中健人, 鈴木博貴, 河内俊憲

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 54th-40th 2022

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Tracking of Shock Wave Position in Two-dimensional Transonic Shock Buffet by Applying Machine Learning and Calculation of Phase-averaged Pressure Propagation Speed

菊池翼, 福本翔太, 田中健人, 竹内孔一, 河内俊憲

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 54th-40th 2022

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Supersonic wind tunnel introducing mainstream turbulence without a Laval nozzle

清水崇史, 福田光一, 田中健人, 鈴木博貴, 河内俊憲

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 54th-40th 2022

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PIV Measurements of Turbulent Boundary Layer at Re_θ =14,000 Developed on a Supersonic Wind Tunnel Wall

貝原涼弥, 田中健人, 鈴木博貴, 河内俊憲

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 54th-40th 2022

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Simultaneous Fast-framing Dual-layer Focusing-schlieren and Unsteady Pressure Sensitive Paint Measurements for a CRM Swept Wing in a Two-dimensional Transonic Wind Tunnel

河内俊憲, 福本翔太, 杉岡洋介, 小池俊輔

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 54th-40th 2022

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再突入カプセルの電磁流体制御に対する壁面の導通の影響に関する3 次元流体解析—Three-Dimensional Fluid Analysis on the Effect of Wall Conduction on MHD Flow Control for Re Entry Capsules

中村, 洸太, 永田, 靖典, 山田, 和彦, 河内, 俊憲, NAKAMURA, Kota, NAGATA, Yasunori, YAMADA, Kazuhiko, KOCHI, Toshinori

令和3年度宇宙航行の力学シンポジウム = Symposium on Flight Mechanics and Astrodynamics: 2021 2021.12

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Language：Japanese Publisher：宇宙航空研究開発機構宇宙科学研究所(JAXA)(ISAS)

令和3年度宇宙航行の力学シンポジウム（2021年12月20日-21日. オンライン開催)
Symposium on Flight Mechanics and Astrodynamics: 2021 (December 20-21, 2021. Online Meeting)
資料番号: SA6000174007

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Side-Wall Effects on the Global Stability of Swept and Unswept Supercritical Wings at Buffet Conditions

SANSICA Andrea, HASHIMOTO Atsushi, KOIKE Shunsuke, KOCHI Toshinori

宇宙航空研究開発機構特別資料: 流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2020オンライン論文集 = JAXA Special Publication: Proceedings of Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2020 Online JAXA-SP-20-008 ( 20 ) 109 - 118 2021.2

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Language：English Publisher：Japan Aerospace Exploration Agency (JAXA)

Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2020 Online (September 28-30, 2020. The Japan Society for Aeronautical and Space Sciences : Japan Aerospace Exploration Agency (JAXA), Online meeting)A fully three-dimensional (3D) RANS-based global stability analysis is performed on wings in the presence of side-walls to study the complex interaction between buffet shock-oscillations, buffet cells and corner separations. A validation of both the nonlinear and linear stability analysis solvers is given for a two-dimensional (2D) incompressible laminar cylinder and for turbulent transonic buffet on a 2D OAT15A airfoil. The numerical setup is based on the experiments conducted at JAXA 0.8 m × 0.45 m high Reynolds number transonic wind tunnel on a 2D Common Research Model (CRM) profile. The CRM profile is extruded in the spanwise direction and flash mounted on lateral walls at its extremities. An unswept and a swept configuration at sweep angle of 10 deg are considered. The effect of the angle of attack (AoA) is studied for both configurations by selecting AoA = 4 and 7 deg. The RANS solutions are compared against the experimental oil-flow visualizations. Despite some differences in terms of size of the corner separation and shock locations, the main flow features are captured. For the unswept case, the results show that the separation in the middle wing section and corners increases with the AoA. Since the flow slows down near the side-walls, the shock is weakened and moves upstream towards the leading edge. When a sweep angle is applied, the flow is distorted by a crossflow velocity component that causes the corner separations to increase or decrease depending on the boundary-layer thickness of the secondary flow created in the wing spanwise direction. Linear global stability calculations carried out on the unswept wing at the lowest AoA show the presence of a 2D oscillatory mode at St approx. = 0.06 that is spatially localized on the shock. Another unstable mode at higher frequencies (St approx. = 0.1) is located near the corner separations and perturbation packets travel downstream along the shear-layer. For the highest AoA, the 2D mode no longer exists and two 3D modes at higher frequencies appear (St approx. = 0.07 and St approx. = 0.2). These modes are organized in spanwise perturbation wavepackets generated from the corner separation and convected downstream towards the wing middle section. In the separated region in the wing mid-section, the perturbations travel upstream from the trailing-edge towards the shock. Future investigations will focus on the effect of the sweep angle and detection of buffet cells.Physical characteristics: Original contains color illustrations

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Fast-framing Focusing-schlieren Flow Visualization of a CRM Swept Wing in a Two-dimensional Transonic Wind Tunnel

河内俊憲, 大寺健吾, 福本翔太, 杉岡洋介, 小池俊輔

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 53rd-39th 2021

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Extracting Principal Modes of Two-dimensional Shock Buffet by Using Dynamic Mode Decomposition

福本翔太, 河内俊憲, 大寺健吾, 杉岡洋介

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 53rd-39th ( 3 ) 82 - 92 2021

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Language：Japanese Publisher：THE JAPAN SOCIETY FOR AERONAUTICAL AND SPACE SCIENCES

Self-oscillation of a shock wave, which is called a transonic shock buffet, occurs on a wing surface in a transonic flow. Lee and Crouch explained the self-sustained mechanism by different pressure wave propagations but there is no experimental evidence of which feedback loop is dominant. The principal aim of the present study is to identify the dominant feedback path of pressure waves related to the shock buffet using high-speed focusing schlieren movies. The experimental data showed that the flow fields include complicated phenomena such as a lot of pressure waves with a broad range of frequency. Therefore, we performed dynamic mode decomposition (DMD) analysis to extract dominant phenomena for the buffet. DMD modes whose frequencies corresponded to the shock oscillation frequencies were extracted and investigated. DMD modes revealed that pressure perturbations generated at the shock foot and the perturbation propagated to the height-wise direction along with the shock wave. This feedback pass is similar to that observed by Crouch using the global stability analysis for NACA 0012 airfoil.

DOI： 10.2322/jjsass.70.82

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Unsteady Pressure-Sensitive Paint Measurement on a CRM Swept Wing in Two-Dimensional Transonic Wind Tunnel

杉岡洋介, 小池俊輔, 河内俊憲

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 53rd-39th 2021

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Visualization of Combustion Phenomena by the Camera mounted directly on the Scramjet Engine

細谷昌平, 永田靖典, 河内俊憲, 竹腰正雄, 高橋政浩, 富岡定毅

宇宙科学技術連合講演会講演集(CD-ROM) 65th 2021

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Simultaneous two-section visualization by fault schlieren of two-dimensional swept wing Buffet

大寺健吾, 河内俊憲, 福本翔太, 杉岡洋介, 小池俊輔

飛行機シンポジウム講演集(CD-ROM) 59th 2021

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Evaluation of turbulent statistics in supersonic jet fields using Laser Speckle Velocimetry

中川貴裕, 丸山裕也, 河内俊憲

宇宙科学技術連合講演会講演集(CD-ROM) 65th 2021

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Focusing schlieren and schlieren imaging of the convection velocity of large-scale structure

IWACHIDO Masaki, KOUCHI Toshinori, YANASE Shinichiro, NAKANISHI Yusuke

The Proceedings of Conference of Chugoku-Shikoku Branch 2021.59 07b1 2021

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Language：Japanese Publisher：The Japan Society of Mechanical Engineers

DOI： 10.1299/jsmecs.2021.59.07b1

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Experimental Investigation on Effect of Freestream Turbulence on A Supersonic Jet-field

丸山裕也, 河内俊憲, 中川貴裕, 青木礼

宇宙科学技術連合講演会講演集(CD-ROM) 65th 2021

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機械工学年鑑2020 第7章流体工学 7.1 圧縮性流れ

河内俊憲

2020.7

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VSL Analysis and Influence on Trajectory of Electrodynamic Heat Shield Atmospheric Entry Capsule

永田靖典, 前田真吾, 河内俊憲

宇宙科学技術連合講演会講演集(CD-ROM) 64th 2020

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Control of large-scale vortices occurring in the semiconductor wafer cleaner

KOUCHI Toshinori, AOYAMA Tsubasa, NAGATA Yasunori, YANASE Shinichiro

The Proceedings of Conference of Chugoku-Shikoku Branch 2020.58 05b5 2020

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DOI： 10.1299/jsmecs.2020.58.05b5

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Effect of LES resolution for inner layer in turbulent boundary layer on supersonic wall injection

HASHIMOTO Tomoyuki, KOUCHI Toshinori, NAGATA Yasunori, YANASE Shinichiro, AOKI Rei

The Proceedings of Conference of Chugoku-Shikoku Branch 2020.58 05c2 2020

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DOI： 10.1299/jsmecs.2020.58.05c2

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CFD analysis on MHD control effect of model surface conductivity in weakly ionized plasma flow

SHIMIZU Daichi, NAGATA Yasunori, KOUCHI Toshinori, YANASE Shinichiro, NORII Takumi

The Proceedings of Conference of Chugoku-Shikoku Branch 2020.58 05c3 2020

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DOI： 10.1299/jsmecs.2020.58.05c3

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An experimental study of relationship between CNF viscosity characteristics and pipe friction

YAMANE Eisuke, KOUCHI Toshinori, YANASE Shinichiro, NAGATA Yasunori, YASUDA Kazunori

The Proceedings of Conference of Chugoku-Shikoku Branch 2020.58 05a5 2020

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DOI： 10.1299/jsmecs.2020.58.05a5

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VSL Analysis of Atmospheric Entry Capsule with Electrodynamic Heat Shield

NAGATA Yasunori, MAEDA Shingo, KOUCHI Toshinori, YANASE Shinichiro

The Proceedings of Mechanical Engineering Congress, Japan 2020 S19104 2020

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The electrodynamic heat shield is a new type of heat protection system for the atmospheric-entry vehicle, which utilizes the Lorentz force acting on the weakly ionized plasma flow inside the shock layer. We are developing the Viscous Shock Layer (VSL) analysis method for an electrodynamic heat shield for quick estimation of performance, including the effect on the reentry trajectory. In this study, we propose the chemical non-equilibrium VSL equations for the electrodynamic heat shield analysis and compare its result to CFD calculation and theoretical relationship. In proposed VSL equations, momentum and energy equations have additional terms, and species conservation equations have no change. Inside the shock layer, ionization reaction is occurred due to high temperature, and electrical conductivity is changed by the flow condition, such as altitude and flow velocity. VSL results in the case of several altitudes of reentry trajectory agree with CFD results on electrical conductivity estimation. And, the stagnation heat flux diminish rates also agree with the theoretical relationship based on the interaction parameter Q. Therefore, our VSL analysis method can estimate the effect of electrodynamic heat shield depending on the flow condition.

DOI： 10.1299/jsmemecj.2020.s19104

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Introduction of Fluid Dynamics Laboratory in Okayama University

47 ( 8 ) 507 - 512 2019.8

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An experimental study of the drag reduction pipe flows with the addition of natural macromolecules

柳瀬眞一郎, 山根映介, 河内俊憲, 永田靖典, 保田和則

日本機械学会流体工学部門講演会講演論文集(CD-ROM) 97th 2019

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Influence of Free-stream Turbulence on Supersonic Jet Mixing

河内俊憲, 大元朝斗, 宮井祥真, 永田靖典, 柳瀬眞一郎

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 51st-37th 2019

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LES Analysis of Influence of Free-stream Turbulence on Supersonic Jet Mixing

永田靖典, 横井聖太朗, 片山智耀, 河内俊憲, 柳瀬眞一郎

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 51st-37th 2019

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Shock-induced Separation and Shockwave Oscillation on Swept and Unswept Two-Dimensional Common Research Model Wings

小池俊輔, 松本葉, 河内俊憲

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 51st-37th 2019

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Velocimetry in Supersonic Flows Using Acetone Condensation Nanoparticle

河内俊憲, 永田靖典, 柳瀬眞一郎

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 51st-37th 2019

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吸込みバルブ周りの脈動流れ

佐々木翼, 高見敏弘, 柳瀬眞一郎, 河内俊憲

ターボ機械協会講演会(CD-ROM) 82nd 2019

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Measurement of Turbulence in Supersonic Flow by the Shadowgraph Method

香取幸汰, 細谷昌平, 真殿健広, 河内俊憲, 永田靖典, 柳瀬眞一郎, 富岡定毅, 小林完

宇宙科学技術連合講演会講演集(CD-ROM) 63rd 2019

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Convection speed of large scale structure in ejector jet

松本葉, 中矢雅人, 井上広夢, 河内俊憲, 永田靖典, 柳瀬眞一郎

宇宙科学技術連合講演会講演集(CD-ROM) 63rd 2019

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LES解析における主流乱れの超音速噴流混合への影響

永田靖典, 横井聖太朗, 青木礼, 河内俊憲, 柳瀬眞一郎

数値流体力学シンポジウム講演論文集(CD-ROM) 33rd 2019

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小型超音速風洞内にワイヤー格子を設置した流れのRANSによる数値解析

大島渉, 永田靖典, 河内俊憲, 柳瀬眞一郎

数値流体力学シンポジウム講演論文集(CD-ROM) 33rd 2019

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フラクタル格子乱流場のPIV計測とその妥当性の検証

宮里健志, 柳瀬眞一郎, 河内俊憲, 永田靖典, 中野和輝

日本機械学会中国四国支部総会・講演会講演論文集(CD-ROM) 57th 2019

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凝集ナノ粒子を用いた超音速流れの可視化とPIVに関する研究

福田征弥, 柳瀬眞一郎, 河内俊憲, 永田靖典, 宮井祥真

日本機械学会中国四国支部総会・講演会講演論文集(CD-ROM) 57th 2019

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RANSを用いた低レイノルズ数域における翼型NACA0012の二次元解析

井上佑希, 永田靖典, 河内俊憲, 柳瀬眞一郎

日本機械学会中国四国支部総会・講演会講演論文集(CD-ROM) 57th 2019

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超音速電磁流体制御におけるアークジェット気流サイズの影響に関する実験的研究

市川恒士, 永田靖典, 河内俊憲, 柳瀬眞一郎

日本機械学会中国四国支部総会・講演会講演論文集(CD-ROM) 57th 2019

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A study of vortical structures occurring in a semiconductor wafer cleaner

河内俊憲, 青山翼, 永田靖典, 柳瀬眞一郎

日本機械学会流体工学部門講演会講演論文集(CD-ROM) 97th 2019

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Numerical Study of the Flow in the Semiconductor Wafer Cleaner by OpenFOAM

柳瀬眞一郎, 青山翼, 河内俊憲, 永田靖典, 三好勇輝

日本機械学会流体工学部門講演会講演論文集(CD-ROM) 96th 2018

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Condensation Nano-particle Flow Visualization in Supersonic Boundary Layer

河内俊憲, 福田征弥, 永田靖典, 柳瀬眞一郎

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 50th-36th 2018

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Combined fast-framing schlieren imaging and PIV measurements of shock wave-boundary layer interaction

溝口真由, 渡部達也, 河内俊憲, 永田靖典, 柳瀬眞一郎

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 50th-36th 2018

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修正force-coupling methodを用いた二気泡間の相互作用に関する数値解析

上西雅信, GUAN Chao, 柳瀬眞一郎, 河内俊憲, 永田靖典

日本機械学会中国四国支部総会・講演会講演論文集(CD-ROM) 56th 2018

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フラクタル格子乱流の熱線風速計とPIVによる計測

平尾将孝, 柳瀬眞一郎, 河内俊憲, 永田靖典, 宮里健志

日本機械学会中国四国支部総会・講演会講演論文集(CD-ROM) 56th 2018

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Control of Electrodynamic Heat Shield using Capsule Surface Conductivity

永田靖典, 乗井拓己, 河内俊憲, 柳瀬眞一郎

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 50th-36th 2018

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Numerical Study of the Vortical Structures in the Pump Sump

柳瀬眞一郎, 山崎諒, 河内俊憲, 永田靖典, 細田駿介

日本機械学会流体工学部門講演会講演論文集(CD-ROM) 96th 2018

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気中衝突水噴流の数値解析と実験による検証

徳善一仁, 高崎玲爾, 柳瀬眞一郎, 河内俊憲, 永田靖典

日本機械学会中国四国支部総会・講演会講演論文集(CD-ROM) 55th 2017

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固体状表面およびすべり表面を有する球形気泡運動の修正Force-coupling Methodによる数値解析

GUAN Chao, 柳瀬眞一郎, 松浦宏治, 河内俊憲, 永田靖典

数値流体力学シンポジウム講演論文集(CD-ROM) 31st 2017

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PLIFを用いた超音速境界層内の変動密度計測

大元朝斗, 松永明, 佐藤直也, 河内俊憲, 永田靖典, 柳瀬眞一郎

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 49th-35th 2017

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衝撃波上流域の速度変化がバフェットに及ぼす影響

山下雄輝, 河内俊憲, 小池俊輔, 柳瀬眞一郎

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 49th-35th 2017

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ステレオPIVとシュリーレンを用いた超音速境界層内の同時計測

溝口真由, 山内一樹, 河内俊憲, 永田靖典, 柳瀬眞一郎

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 49th-35th 2017

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二次元問題を用いた衝撃波捕獲方法の評価

堀江亮太, 河内俊憲, 永田靖典, 柳瀬眞一郎

日本機械学会中国四国支部総会・講演会講演論文集(CD-ROM) 55th 2017

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Force-coupling methodによる気泡と壁面の相互作用に関する研究

GUAN Chao, 柳瀬眞一郎, 河内俊憲, 永田靖典, 松浦宏治

日本機械学会中国四国支部総会・講演会講演論文集(CD-ROM) 54th 2016

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超音速流れへのトルエンPLIFの適用

松永明, 佐藤直也, 河内俊憲, 永田靖典, 柳瀬眞一郎

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 48th-34th 2016

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非定常シュリーレン計測結果に基づいたLeeの遷音速バフェットモデルの修正

河内俊憲, 山口真伍, 小池俊輔, 柳瀬眞一郎

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 48th-34th 2016

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マイクロバブルを含む円管内流の抵抗係数測定

岡本拓也, 庄田圭佑, 河内俊憲, 永田靖典, 柳瀬眞一郎

日本機械学会流体工学部門講演会講演論文集(CD-ROM) 94th 2016

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マイクロフォンを用いた半導体洗浄装置モデル内に形成される大規模渦構造の検出

三好勇輝, 中野裕介, 河内俊憲, 永田靖典, 柳瀬眞一郎

日本機械学会流体工学部門講演会講演論文集(CD-ROM) 94th 2016

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LESを用いた超音速せん断層内の乱流混合プロセス解析

鎌倉大樹, 河内俊憲, 永田靖典, 柳瀬眞一郎

日本機械学会中国四国支部総会・講演会講演論文集(CD-ROM) 54th 2016

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スーパークリティカル翼における衝撃波自励振動のモデル

山口真伍, 河内俊憲, 柳瀬眞一郎, 小池俊輔, 中島努, 佐藤衛, 神田宏

日本機械学会中国四国支部総会・講演会講演論文集(CD-ROM) 54th 2016

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焼却炉内の放射性セシウムを含む廃棄物燃焼過程の数値解析

柳瀬眞一郎, 杉杖典岳, 石森有, 横山薫, 小原義之, 高橋信雄, RONG Degang, 竹田宏, 河内俊憲, 高見敏弘, 桑木賢也, 百武徹, 藤村薫

日本機械学会計算力学講演会論文集(CD-ROM) 28th 2015

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超音速境界層内における大規模構造の移流速度計測

山内一樹, 河合辰哉, 河内俊憲, 永田靖典, 柳瀬眞一郎

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 47th-33rd 2015

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遷音速二次元翼バフェットにおける衝撃波と同期する音波の解析

山口真伍, 河内俊憲, 柳瀬眞一郎, 小池俊輔, 中島努, 佐藤衛, 神田宏

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 47th-33rd 2015

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超音速風洞を用いた低温域におけるトルエンの蛍光特性取得

佐藤直也, 河内俊憲, 永田靖典, 柳瀬眞一郎, 阿倍浩司

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 47th-33rd 2015

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二次元遷音速バフェットのウェーブレット解析-ボルテックス・ジェネレータの効果に関して-

河内俊憲, 山口真伍, 柳瀬眞一郎, 小池俊輔, 中島努, 佐藤衛, 神田宏

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 47th-33rd 2015

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温度及び周囲ガス組成がトルエン蛍光に及ぼす影響について

阿部浩司, 河内俊憲, 佐藤直也, 浅井圭介

日本機械学会流体工学部門講演会講演論文集(CD-ROM) 93rd 2015

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Visualization in the axisymmetric supersonic ejector by focusing schlieren

関谷洸希, 山口真伍, 河内俊憲, 柳瀬眞一郎, 永田靖典

可視化情報学会誌 35 ( Suppl.1 ) 2015

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流量一定条件を課した曲がり管内流の数値計算

益田卓哉, 永田靖典, 河内俊憲, 早水庸隆, 柳瀬眞一郎

日本機械学会中国四国支部総会・講演会講演論文集(CD-ROM) 53rd 2015

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二次元遷音速バフェットの可視化によるVortex Generatorの効果の解明

笠木信哉, 山口真伍, 河内俊憲, 柳瀬眞一郎, 小池俊輔, 中島努, 佐藤衛, 神田宏

日本機械学会中国四国支部総会・講演会講演論文集(CD-ROM) 53rd 2015

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半導体洗浄機モデル内の渦構造の時間変化

清水義也, 柳瀬眞一郎, 河内俊憲, 森洋平, 福田修也, 中野裕介

日本機械学会年次大会講演論文集(CD-ROM) 2014 2014

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高速度フォーカシングシュリーレンによる二次元翼バフェットの可視化とその解析

山口真伍, 河内俊憲, 柳瀬眞一郎, 小池俊輔, 中島務, 佐藤衛, 神田宏

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 46th-32nd 2014

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焼却設備でのセシウム挙動解析(7)高セシウム濃度の生活ごみに関するシミュレーション

横山薫, 小原義之, 杉杖典岳, 高橋信雄, RONG Degang, 竹田宏, 河内俊憲, 柳瀬眞一郎, 桑木賢也, 高見敏弘, 百武徹

日本原子力学会秋の大会予稿集(CD-ROM) 2014 2014

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焼却設備でのセシウム挙動解析(5)焼却設備から発生する焼却灰の分析

横山薫, 小原義之, 杉杖典岳, 高橋信雄, RONG Degang, 竹田宏, 河内俊憲, 柳瀬眞一郎, 桑木賢也, 高見敏弘, 百武徹

日本原子力学会秋の大会予稿集(CD-ROM) 2014 2014

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焼却設備でのセシウム挙動解析(6)焼却設備内でのセシウム挙動のシミュレーション

横山薫, 小原義之, 杉杖典岳, 高橋信雄, RONG Degang, 竹田宏, 河内俊憲, 柳瀬眞一郎, 桑木賢也, 高見敏弘, 百武徹

日本原子力学会秋の大会予稿集(CD-ROM) 2014 2014

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焼却炉内での放射性Cs挙動解析(2)焼却炉内でのCsの凝集および灰への付着モデル構築

河内俊憲, 柳瀬眞一郎, 百武徹, 桑木賢也, 高見敏弘, RONG Degang, 竹田宏, 高橋信雄, 横山薫, 小原義之, 杉杖典岳

流動化・粒子プロセッシングシンポジウム講演論文集 20th 2014

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焼却炉内での放射性Cs挙動解析(1)福島県内の焼却施設を対象とした実灰調査

高橋信雄, 横山薫, 小原義之, 杉杖典岳, RONG Degang, 竹田宏, 河内俊憲, 柳瀬眞一郎, 桑木賢也, 高見敏弘, 百武徹

流動化・粒子プロセッシングシンポジウム講演論文集 20th 2014

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焼却炉内での放射性Cs挙動解析(3)福島県内の焼却炉内のCs挙動解析

高見敏弘, 桑木賢也, RONG Degang, 竹田宏, 河内俊憲, 柳瀬眞一郎, 百武徹, 高橋信雄, 横山薫, 小原義之, 杉杖典岳

流動化・粒子プロセッシングシンポジウム講演論文集 20th 2014

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DEM-CFDカップリングモデルに基づく焼却炉での燃焼流れ数値シミュレーション

桑木賢也, 大本啓貴, 高見敏弘, RONG Degang, 竹田宏, 柳瀬眞一郎, 河内俊憲, 百武徹, 横山薫, 杉杖典岳, 小原義之, 高橋信雄

流動化・粒子プロセッシングシンポジウム講演論文集 20th 2014

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粒子群を含む流れのカオス的挙動に関する数値的研究

新庄弘明, 柳瀬眞一郎, 河内俊憲

日本機械学会中国四国支部総会・講演会講演論文集(CD-ROM) 52nd 2014

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福島県内の焼却炉内のCs挙動解析

柳瀬眞一郎, 河内俊憲, 杉杖典岳, 横山薫, 小原義之, 高橋信雄, RONG D., 竹田宏, 百武徹, 桑木賢也, 高見敏弘

日本機械学会年次大会講演論文集(CD-ROM) 2014 2014

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放射性物質を含む廃棄物焼却の燃焼シミュレーションの検討

桑木賢也, 高見敏弘, 横山薫, 小原義之, 杉杖典岳, 栄徳剛, 竹田宏, 百武徹, 河内俊憲, 柳瀬眞一郎

化学工学会秋季大会研究発表講演要旨集(CD-ROM) 45th 2013

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枚葉式シリコンウエハ洗浄装置モデルのOpenFOAMによる数値計算

久米田高輝, 清水義也, 森洋平, 福田修也, 河内俊憲, 柳瀬眞一郎

日本機械学会中国四国支部総会・講演会講演論文集(CD-ROM) 51st 2013

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半導体洗浄機モデル内流れのPIV計測

清水義也, 柳瀬眞一郎, 河内俊憲, 森洋平, 福田修也

日本機械学会年次大会講演論文集(CD-ROM) 2013 2013

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超音速噴流場における乱流拡散の評価のためのPIV-LIF同時計測

河内俊憲, 柳瀬眞一郎, 岡慶典, 升谷五郎

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 45th-2013 2013

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超音速流中へ垂直に噴射した水素の燃焼状態のLES解析

渡部潤也, 河内俊憲, 滝田謙一, 升谷五郎

燃焼シンポジウム講演論文集 50th 2012

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エジェクタジェットの二次燃焼効率改善を目指したPIVによる速度場計測

野島清志, 河内俊憲, 升谷五郎, 富岡定毅

日本機械学会東北支部総会・講演会講演論文集 47th 2012

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直結式デュアルモードスクラムジェット内の断層シュリーレンによる可視化

河内俊憲, GOYNE Christopher, ROCKWELL Robert, MCDANIEL James

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 44th-2012 2012

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変動速度の空間相関を用いた超音速噴射流れ場の解析

浦本翔平, 河内俊憲, 升谷五郎

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 44th-2012 2012

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水素/メタン混合燃料のエッジフレームに関する研究

徳永真人, 西脇渉, 滝田謙一, 河内俊憲

燃焼シンポジウム講演論文集 50th 2012

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LES of Jet Turbulent Mixing in Supersonic Flow

渡部潤也, 河内俊憲, 滝田謙一, 升谷五郎

宇宙航空研究開発機構特別資料 JAXA-SP- ( 10-012 ) 2011

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条件付PIV測定による擬似衝撃波内に噴射した気体の混合特性評価

高江剛一, 渡部潤也, CHOI Byugil, 河内俊憲, 升谷五郎

日本航空宇宙学会北部支部講演会ならびに再使用型宇宙推進系シンポジウム講演論文集 2011-12th 2011

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PIVを用いた軸対称超音速エジェクタのエントレインメント計測

保坂春樹, 野島清志, 河内俊憲, 升谷五郎

日本航空宇宙学会北部支部講演会ならびに再使用型宇宙推進系シンポジウム講演論文集 2011-12th 2011

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アセトンPLIFによる擬似衝撃波中に噴射された垂直噴流の挙動の観察

岡慶典, 阿部浩司, 河内俊憲, 升谷五郎

日本航空宇宙学会北部支部講演会ならびに再使用型宇宙推進系シンポジウム講演論文集 2011-12th 2011

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超音速水素噴流の乱流燃焼過程のLES解析

渡部潤也, 河内俊憲, 滝田謙一, 升谷五郎

燃焼シンポジウム講演論文集 49th 2011

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高速シュリーレンを用いた超音速噴流場のスペクトル解析

河内俊憲, 升谷五郎

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 42nd-2010 2010

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誘電体バリア放電を用いた高速流中での着火促進技術の開発

松原慶典, 山本貴正, 岡崎慈, 河内俊憲, 滝田謙一

日本航空宇宙学会北部支部講演会ならびに再使用型宇宙推進系シンポジウム講演論文集 2010-11th 2010

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超音速噴射流れ場のステレオPIV計測

津留真一郎, 浦本翔平, 河内俊憲, 升谷五郎

日本航空宇宙学会北部支部講演会ならびに再使用型宇宙推進系シンポジウム講演論文集 2010-11th 2010

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ステレオPIVを用いた超音速流れ場の境界層速度計測

浦本翔平, 津留真一郎, 河内俊憲, 升谷五郎

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 42nd-2010 2010

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コーナー・バンプを設置した矩形ダクトにおける擬似衝撃波の安定性

星野貴久, 河内俊憲, 升谷五郎

宇宙科学技術連合講演会講演集(CD-ROM) 54th 2010

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ロケット複合エンジン設計課題解決に掛かる要素研究の状況

富岡定毅, 杉尾隆, 野島清志, 河内俊憲, 永冨晋也, 小林輝男, 松尾亜紀子

宇宙科学技術連合講演会講演集(CD-ROM) 54th 2010

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エッジフレームの局所伸長率に及ぼすルイス数の効果

西脇渉, 望月宏朗, 滝田謙一, 河内俊憲

燃焼シンポジウム講演論文集 48th 2010

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超音速燃焼器における水素およびエチレン燃料の乱流混合過程のLES解析

渡部潤也, 河内俊憲, 滝田謙一, 升谷五郎

燃焼シンポジウム講演論文集 48th 2010

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超音速流中における誘電体バリア放電に及ぼす主流マッハ数の影響

岡崎慈, 松原慶典, 山本貴正, 滝田謙一, 河内俊憲

燃焼シンポジウム講演論文集 48th 2010

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超音速流中における噴流の乱流混合のLES解析

渡部潤也, 河内俊憲, 滝田謙一, 升谷五郎

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 42nd-2010 2010

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エジェクタ・ラムジェットの二次燃料分布

野島清志, 河内俊憲, 升谷五郎, 富岡定毅

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 42nd-2010 2010

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超音速流れ場における速度変動量のPIV測定

田村武, 津留真一郎, 小池俊輔, 河内俊憲, 升谷五郎

日本航空宇宙学会北部支部講演会ならびに再使用型宇宙推進系シンポジウム講演論文集 2009-10th 2009

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超音速横風中のパルス噴射において観測された噴流貫通のヒステリシス

河内俊憲, 升谷五郎, 柴山博治, 星野貴久

日本航空宇宙学会北部支部講演会ならびに再使用型宇宙推進系シンポジウム講演論文集 2009-10th 2009

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非平衡プラズマを用いた高速流中での着火促進法の開発

山本貴正, 松原慶典, 滝田謙一, 河内俊憲

燃焼シンポジウム講演論文集 47th 2009

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擬似衝撃波による燃料混合メカニズムの研究

CHOI Byoungil, 山内英樹, 河内俊憲, 升谷五郎

日本航空宇宙学会北部支部講演会ならびに再使用型宇宙推進系シンポジウム講演論文集 2009-10th 2009

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Penetration Characteristics of Pulsed Jet in Supersonic Crossflow

柴山博治, 河内俊憲, 升谷五郎

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集 40th-2008 2008

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超音速燃焼器における円形噴射孔とStinger型噴射孔の燃焼性能比較試験

平野昂志, 河内俊憲, 工藤賢司, 村上淳郎, 加藤周徳, 富岡定毅, 松尾亜紀子

日本航空宇宙学会北部支部講演会講演論文集 2008 2008

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窒素/酸素混合作動ガスPJの高亜音速流における着火特性

松原慶典, BOSSARD Pierre-Edouard, 滝田謙一, 河内俊憲

燃焼シンポジウム講演論文集 46th 2008

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Assessments of Jet Penetrations into Supersonic Crossflow Using High-Speed Framing Schlieren Images

河内俊憲, 柴山博治, 升谷五郎

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集 40th-2008 2008

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超音速流中でのパルス噴射の貫通と混合

河内俊憲, 泉川宗男, 櫻中登, 富岡定毅

日本航空宇宙学会北部支部講演会講演論文集 2007 2007

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Numerical Prediction of RBCC Engine Pumping Performance Under Sea Level Static

河内俊憲, 富岡定毅, 苅田丈士

航空原動機・宇宙推進講演会講演論文集(CD-ROM) 47th 2007

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超音速主流に対する垂直噴流の貫通促進を目指した新型噴射孔形状

平野昂志, 松尾亜紀子, 河内俊憲, 泉川宗男, 富岡定毅

日本航空宇宙学会北部支部講演会講演論文集 2007 2007

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超音速燃焼器における燃料噴射孔形状が貫通に及ぼす影響の検討

平野昂志, 河内俊憲, 小池俊輔, 泉川宗男, 松尾亜紀子, 富岡定毅, 升谷五郎

日本流体力学会年会講演アブストラクト集 2007 2007

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超音速流中への直列4孔噴射の貫通特性

小池俊輔, 河内俊憲, 泉川宗男, 富岡定毅, 升谷五郎

燃焼シンポジウム講演論文集 45th 2007

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Numerical Prediction of RBCC Engine Pumping Performance Under Sea Level Static

河内俊憲, 苅田丈士, 富岡定毅

宇宙航空研究開発機構特別資料 JAXA-SP- ( 06-006 ) 2006

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超音速燃焼器における燃料混合促進のための噴射孔形状に関する数値解析

平野昂志, 松尾亜紀子, 富岡定毅, 河内俊憲

数値流体力学シンポジウム講演論文集(CD-ROM) 20th 2006

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ロケット複合エンジンのエジェクタモードにおける始動特性

河内俊憲, 櫻中登, 渡邊修一, 三谷徹, 富岡定毅

日本航空宇宙学会北部支部講演会講演論文集 2006 2006

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Scramjet Performance Achieved in Engine Tests from M4 to M8 Flight Conditions

Tohru Mitani, Sadatake Tomioka, Takeshi Kanda, Nobuo Chinzei, Toshinori Kouchi

12th AIAA International Space Planes and Hypersonic Systems and Technologies 3 1 - 13 2004

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Language：English Publisher：American Institute of Aeronautics and Astronautics

Thrust performances of scramjet engines were compared with theoretical values to quantify the progress in engine performances (defined as "achievement factors", or "factors") from Mach (termed as "M") 4 to M8 flight conditions. An engine with a ramp produced a net thrust of 215 N under the M8 tests and a comparison of a theoretical thrust yielded a thrust achievement factor of 51%. By excluding boundary layer, an engine with a thick strut delivered a net thrust of 560 N and showed a thrust factor of 92% and a net thrust factor of 45%. The thrusts were limited by flow separation caused by engine combustion (termed as "engine unstart"). The starting characteristics was improved by boundary layer controls in M6 and M4 conditions. An engine with a thin strut doubled the thrust from 1620 N to 2460 N by the boundary layer bleeding in the M6 tests. The improved thrust factor was 60% at the stoichiometric H2 condition. Under M4 tests, the net thrust was tripled by the bleed and a two-staged injection of H2. As results, the thrust factor was raised from 53% to 70%, the net thrust factor was increased from 32% to 55%. Studies required for improving the net performance were addressed.

DOI： 10.2514/6.2003-7009

CiNii Article

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Scramjet Engine Performance Attained in RJTF Testing

三谷徹, 富岡定毅, 苅田丈士, 谷香一郎, 鎮西信夫, 河内俊憲

日本航空宇宙学会論文集 52 ( 600 ) 2004

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SUBSCALE WIND TUNNELS AND SUPPLEMENTAL STUDIES OF SCRAMJET ENGINE TESTS.

三谷徹, 平岩徹夫, 苅田丈士, 志村隆, 渡辺修一, 樽川雄一, 河内俊憲, 北村英二郎, 八並知実

航空宇宙技術研究所報告 NAL-TR- ( 1458 ) 2003

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Effects of Boundary-layer Bleeding on Scramjet Performance

河内俊憲, 三谷徹, 小寺正敏, 升谷五郎

日本機械学会流体工学部門講演会講演論文集 81st ( CD-ROM ) 2003

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境界層抽気がスクラムジェット性能に及ぼす影響

河内俊憲, 三谷徹, 小寺正敏, 升谷五郎

日本機械学会流体工学部門講演会講演論文集 81st 2003

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スクラムジェット燃焼の数値実験

三谷徹, 河内俊憲, 小寺正敏, 升谷五郎

燃焼シンポジウム講演論文集 41st 2003

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レイノルズ数のスクラムジェットインレット性能に及ぼす影響

河内俊憲, 三谷徹, 小寺正敏, 升谷五郎

日本航空宇宙学会北部支部講演会講演論文集 2002 2002

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Experiments of Extinction of Counterflow Twin Cylindrical Flames.

滝田謙一, 河内俊憲, 坂口成章, 布施顕太郎, JU Y

日本機械学会流体工学部門講演会講演論文集 79th ( 101-1010 ) 2001

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スクラムジェットエンジンの燃焼性能見積り

三谷徹, 平岩徹夫, 河内俊憲, 升谷五郎

燃焼シンポジウム講演論文集 39th 2001

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Presentations

Side-Wall Effects on the Global Stability of Swept and Unswept Supercritical Wings at Buffet Conditions

SANSICA Andrea, HASHIMOTO Atsushi, KOIKE Shunsuke, KOCHI Toshinori

2021.2.8 Japan Aerospace Exploration Agency (JAXA)

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Event date： 2021.2.8

Language：English

Fluid Dynamics Conference / Aerospace Numerical Simulation Symposium 2020 Online (September 28-30, 2020. The Japan Society for Aeronautical and Space Sciences : Japan Aerospace Exploration Agency (JAXA), Online meeting)A fully three-dimensional (3D) RANS-based global stability analysis is performed on wings in the presence of side-walls to study the complex interaction between buffet shock-oscillations, buffet cells and corner separations. A validation of both the nonlinear and linear stability analysis solvers is given for a two-dimensional (2D) incompressible laminar cylinder and for turbulent transonic buffet on a 2D OAT15A airfoil. The numerical setup is based on the experiments conducted at JAXA 0.8 m × 0.45 m high Reynolds number transonic wind tunnel on a 2D Common Research Model (CRM) profile. The CRM profile is extruded in the spanwise direction and flash mounted on lateral walls at its extremities. An unswept and a swept configuration at sweep angle of 10 deg are considered. The effect of the angle of attack (AoA) is studied for both configurations by selecting AoA = 4 and 7 deg. The RANS solutions are compared against the experimental oil-flow visualizations. Despite some differences in terms of size of the corner separation and shock locations, the main flow features are captured. For the unswept case, the results show that the separation in the middle wing section and corners increases with the AoA. Since the flow slows down near the side-walls, the shock is weakened and moves upstream towards the leading edge. When a sweep angle is applied, the flow is distorted by a crossflow velocity component that causes the corner separations to increase or decrease depending on the boundary-layer thickness of the secondary flow created in the wing spanwise direction. Linear global stability calculations carried out on the unswept wing at the lowest AoA show the presence of a 2D oscillatory mode at St approx. = 0.06 that is spatially localized on the shock. Another unstable mode at higher frequencies (St approx. = 0.1) is located near the corner separations and perturbation packets travel downstream along the shear-layer. For the highest AoA, the 2D mode no longer exists and two 3D modes at higher frequencies appear (St approx. = 0.07 and St approx. = 0.2). These modes are organized in spanwise perturbation wavepackets generated from the corner separation and convected downstream towards the wing middle section. In the separated region in the wing mid-section, the perturbations travel upstream from the trailing-edge towards the shock. Future investigations will focus on the effect of the sweep angle and detection of buffet cells.Physical characteristics: Original contains color illustrations

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Study on visualization and PIV of the supersonic flow using condensation nanoparticles

FUKUDA Seiya, YANASE Shinichiro, KOUCHI Toshinori, NAGATA Yasunori, MIYAI Syouma

The Proceedings of Conference of Chugoku-Shikoku Branch 2019 The Japan Society of Mechanical Engineers

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Event date： 2019

Language：Japanese

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Shock-induced Separation and Shockwave Oscillation on Swept and Unswept Two-Dimensional Common Research Model Wings

小池俊輔, 松本葉, 河内俊憲

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 2019

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Event date： 2019

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Two Dimensional RANS Analysis of NACA0012 Airfoil at Low Reynolds numbers

INOUE Yuki, NAGATA Yasunori, KOUCHI Toshinori, YANASE Shinichiro

The Proceedings of Conference of Chugoku-Shikoku Branch 2019 The Japan Society of Mechanical Engineers

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Event date： 2019

Language：Japanese

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An Experimental Study of Influence of the Arcjet Plume Size on Supersonic MHD Flow Control Effect

ICHIKAWA Koji, NAGATA Yasunori, KOUCHI Toshinori, YANASE Shinichiro

The Proceedings of Conference of Chugoku-Shikoku Branch 2019 The Japan Society of Mechanical Engineers

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Event date： 2019

Language：Japanese

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Hot-wire Anemometer and PIV Measurement of Fractal Grid Turbulence

HIRAO Masataka, YANASE Shinichiro, KOUCHI Toshinori, NAGATA Yasunori, MIYAZATO Takeshi

The Proceedings of Conference of Chugoku-Shikoku Branch 2018 The Japan Society of Mechanical Engineers

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Event date： 2018

Language：Japanese

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Numerical Study of the Vortical Structures in the Pump Sump

The Proceedings of the Fluids engineering conference 2018 The Japan Society of Mechanical Engineers

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Event date： 2018

Language：Japanese

We conducted numerical simulations of the benchmark experiments of the pump sump conducted by Matsui et al. (2006 & 2015) and compared the simulation with the experimental data to investigate the effects of turbulence model, grid density and detection method of the vortices. We determined a threshold of the gas-liquid fraction function of VOF method (α) and the second invariant of velocity gradient tensor (Q2) to detect the air-entraining and submerged vortices by using vorticity, respectively. This method well detected the vortices and well reproduced the experiments for the RANS simulation using SST k-ω model. Large eddy simulation using Smagorinsky model, however, was sensitive to the grid system and difficult to reproduce the experimental vortex structures even for the finest grid system having 3.7 mil-lion cells.

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Numerical Study of the Flow in the Semiconductor Wafer Cleaner by OpenFOAM

YANASE Shinichiro, AOYAMA Tsubasa, KOUCHI Toshinori, NAGATA Yasunori, MIYOSHI Yuki

The Proceedings of the Fluids engineering conference 2018 The Japan Society of Mechanical Engineers

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Event date： 2018

Language：Japanese

In semiconductor production, efficiency and precision of the cleaning process are very important. In this study, we handle "Single Wafer Cleaner" that is one of the washing methods in the way of blowing air to a wafer with a turning disk at a high speed. However, the flow in the device becomes turbulent, which causes the problem that water drops and dusts re-attach to the wafer surface. Therefore, it is necessary to understand the flow in the device exactly to solve this problem. In previous studies, we experimented to establish the method of understanding the flow in the semiconductor wafer cleaner without a covering cup that is used for liquid splash preventing. In this study, numerical calculations were performed to observe the flow in the device to study influence of covering cup and find a suitable turbulence model to simulate the experiment.

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Numerical study of the interaction between two air bubbles by the modified force-coupling method

UENISHI Masanobu, GUAN Chao, YANASE Shinichiro, KOUCHI Toshinori, NAGATA Yasunori

The Proceedings of Conference of Chugoku-Shikoku Branch 2018 The Japan Society of Mechanical Engineers

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Event date： 2018

Language：Japanese

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衝撃波上流域の速度変化がバフェットに及ぼす影響

山下雄輝, 河内俊憲, 小池俊輔, 柳瀬眞一郎

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 2017

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Event date： 2017

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Numerical Analysis of Impinging Water Jet in Air and Experimental Verification

TOKUZEN Kazuhito, TAKASAKI Reiji, YANASE Shinichiro, KOUCHI Toshinori, NAGATA Yasunori

The Proceedings of Conference of Chugoku-Shikoku Branch 2017 The Japan Society of Mechanical Engineers

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Event date： 2017

Language：Japanese

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非定常シュリーレン計測結果に基づいたLeeの遷音速バフェットモデルの修正

河内俊憲, 山口真伍, 小池俊輔, 柳瀬眞一郎

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 2016

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Event date： 2016

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Wavelet analysis of unsteady shock-wave motion on two-dimensional airfoil with vortex generators

Toshinori Kouchi, Shingo Yamaguchi, Shinichiro Yanase, Shunsuke Koike, Tsutomu Nakajima, Mamoru Sato, Hiroshi Kanda

54th AIAA Aerospace Sciences Meeting 2016

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Event date： 2016

Language：English

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スーパークリティカル翼における衝撃波自励振動のモデル

山口真伍, 河内俊憲, 柳瀬眞一郎, 小池俊輔, 中島努, 佐藤衛, 神田宏

日本機械学会中国四国支部総会・講演会講演論文集(CD-ROM) 2016

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Event date： 2016

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1215 Numerical Calculation of Curved Pipe Flow with Constant Flow Flux Condition

MASUDA Takuya, NAGATA Yasunori, KOUCHI Toshinori, HAYAMIZU Yasutaka, YANASE Shinichiro

2015.2.27 The Japan Society of Mechanical Engineers

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Event date： 2015.2.27

Language：Japanese

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遷音速二次元翼バフェットにおける衝撃波と同期する音波の解析

山口真伍, 河内俊憲, 柳瀬眞一郎, 小池俊輔, 中島努, 佐藤衛, 神田宏

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 2015

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Event date： 2015

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二次元遷音速バフェットの可視化によるVortex Generatorの効果の解明

笠木信哉, 山口真伍, 河内俊憲, 柳瀬眞一郎, 小池俊輔, 中島努, 佐藤衛, 神田宏

日本機械学会中国四国支部総会・講演会講演論文集(CD-ROM) 2015

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Event date： 2015

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二次元遷音速バフェットのウェーブレット解析-ボルテックス・ジェネレータの効果に関して-

河内俊憲, 山口真伍, 柳瀬眞一郎, 小池俊輔, 中島努, 佐藤衛, 神田宏

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 2015

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Event date： 2015

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S0530102 Time Evolution of Vortical Structures in the Model of a Semiconductor Cleaner

SHIMIZU Yoshiya, YANASE Shinichiro, KOUCHI Toshinori, MORI Yohei, FUKUDA Naoya, NAKANO Yusuke

Mechanical Engineering Congress, Japan 2014.9.7 The Japan Society of Mechanical Engineers

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Event date： 2014.9.7

Language：Japanese

In a single wafer spin cleaner, the wafer is rotated at high speed to spin off ultrapure water and clean air is blown perpendicular onto the surface to dry the wafer. Interaction between the rotating wafer and blown air generates vortices and the recirculation flow due to the vortices may cause reattachment of contaminants on the wafer surface. Therefore, we experimentally studied vortical structures and the conditions of their formation in a modeled cleaner by using particle image velocimetry (PIV). The model was a 330 mm diameter rotating disk in a 520 mm diameter cylindrical stationary housing, and laminar blown air came from the housing inlet onto the rotating disk. The angular speed of the rotating disk was changed up to 500 rpm and the blown air rate was 0.5 m3/min. Our PIV data show that turbulent kinetic energy near the housing wall with a vortex is as large as that around the rotating disk around at SOOrpm. This vortex may cause reattachment of particles onto the wafer. The vortices generated in the experimental apparatus have three-dimensional structures regardless of their size.

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901 Numerical simulation on the chaotic behavior of a flow containing particles

SHINJO Hiroaki, YANASE Shinichiro, KOUCHI Toshinori

2014 The Japan Society of Mechanical Engineers

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Event date： 2014

Language：Japanese

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高速度フォーカシングシュリーレンによる二次元翼バフェットの可視化とその解析

山口真伍, 河内俊憲, 柳瀬眞一郎, 小池俊輔, 中島務, 佐藤衛, 神田宏

流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム講演集(CD-ROM) 2014

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Event date： 2014

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S055015 PIV Measurements of the Model of a Semiconductor Cleaning Equipment

SHIMIZU Yoshiya, YANASE Shinichiro, KOUCHI Toshinori, MORI Yohei, FUKUDA Naoya

Mechanical Engineering Congress, Japan 2013.9.8 The Japan Society of Mechanical Engineers

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Event date： 2013.9.8

Language：Japanese

The cleaning process of a silicon wafer is important in the manufacturing of semiconductors, which determines the quality of the final products crucially. In the so-called single wafer cleaning, a wafer washed with cleaning solution and rinse liquid is dried up by rotating at a high speed. We made an experimental apparatus which has a similar structure to the single wafer cleaning chamber, and measured the velocity field in the chamber by the particle image velocimetry(PI V) method.

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133 PIV Measurements in Ejector-Jet to Improve Combustion Efficiency of Secondary Fuel

Nojima Kiyoshi, Kouchi Toshinori, Masuya Goro, Tomioka Sadataka

2012.3.13 The Japan Society of Mechanical Engineers

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Event date： 2012.3.13

Language：Japanese

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A plasma jet assisted combustion with a backward- facing step by fuel injection locations

Chae-Hyoung Kim, In-Seuck Jeung, Byungil Choi, Toshinori Kouchi, Kenichi Takita, Goro Masuya

The 33rd International Symposium on Combustion 2010

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Event date： 2010

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The Effect of a Vent Slot Mixer with a Plasma Jet Torch in the Supersonic Combustion

C. Kim, I. Jeung, B. Choi, T. Kouchi, G. Masuya

46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 2010

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Event date： 2010

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Development of Ignition Enhance Method by Using Non-Equilibrium Plasma in High Speed Flow

T. Yamamoto, Y. Matsubara, K. Takita, T. Kouchi

Asian Joint Conference on Propulsion and Power 2010

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Event date： 2010

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Numerical Simulation of Pulsed Injection into a Supersonic Crossflow

K. Sasaya, J. Watanabe, T. Kouchi, G. Masuya

Asian Joint Conference on Propulsion and Power 2010

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Event date： 2010

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Effects of Injectant Species on Compressible Tubulent Scalar Mixing Structure

Y. Horikoshi, H. Takahashi, T. Kouchi, G. Masuya

Asian Joint Conference on Propulsion and Power 2010

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Event date： 2010

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Stereoscopic PIV Measurement of Supersonic Injection Flowfield and Its Error Analysis

S. Uramoto, S. Tsuru, T. Kouchi, G. Masuya

Asian Joint Conference on Propulsion and Power 2010

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Event date： 2010

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Development of a New Supersonic Mixier for Dual- Mode Scramjet Engine Combustor

C. Kim, I. Jeung, B. Choi, Y. Matsubara, T. Kouchi, G. Masuya

16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference 2009

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Event date： 2009

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Mechanism of mixing enhanced by pseudo-shock wave

Hideki Yamauchi, Byongil Choi, Toshinori Kouchi, Goro Masuya

47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2009

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Event date： 2009

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超音速流れ場における速度変動量のPIV測定

田村武, 津留真一郎, 小池俊輔, 河内俊憲, 升谷五郎

日本航空宇宙学会北部支部講演会ならびに再使用型宇宙推進系シンポジウム講演論文集 2009

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Event date： 2009

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Scalar spatial correlations in a supersonic mixing flowfield

Hidemi Takahashi, Hiroki Oso, Toshinori Kouchi, Goro Masuya, Mitsutomo Hirota

47th AIAA Aerospace Sciences Meeting including the New Horizons Forum and Aerospace Exposition 2009

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Event date： 2009

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Influence of Velocity Fields on Mixing in Pseudo-Shock Wave

Goro Masuya, Byongil Choi, Hideki Yamauchi, Toshinori Kouchi

19th ISABE conference 2009

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Event date： 2009

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Supersonic Combustion with Supersonic Injection Through Diamond-Shaped Orifices

Sadatake Tomioka, Toshinori Kouchi, Ryo Masumoto, Muneo Izumikawa, Akiko Matsuo

45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2009

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Event date： 2009

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Scalar Spatial Correlations in a Supersonic Mixing Flowfield

Hidemi Takahashi, Hiroki Oso, Toshinori Kouchi, Goro Masuya

47th AIAA Aerospace Sciences Meeting including The New Horizons Forum and Aerospace 2009

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Event date： 2009

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Time-space trajectory of unsteady jet into supersonic crossflow using high-speed framing schlieren images

Toshinori Kouchi, Takahisa Hoshino, Keita Sasaya, Goro Masuya

16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference 2009

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Event date： 2009

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Combustion performance of supersonic combustor with stinger-shaped fuel injector

T. Kouchi, K. Hirano, A. Matsuo, K. Kobayashi, S. Tomioka, M. Izumikawa

44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2008

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Event date： 2008

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Matched Pressure Injections into a Supersonic Crossflow through Diamond-Shaped Orifices

Sadatake, T, Kouchi, T, Izumikawa, M, Koike, S, Masuya., G, Hirano, K, Matsuo, A

43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2007

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Event date： 2007

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New Injector Geometry for Penetration Enhancement of Perpendicular Jet into Supersonic Flow

K. Hirano, A. Matsuo, T. Kouchi, S. Tomioka, M. Izumikawa

43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2007

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Event date： 2007

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Pulsed transverse injection applied to a supersonic flow

Toshinori Kouchi, Noboru Sakuranaka, Muneo Izumikawa, Sadatake Tomioka

Collection of Technical Papers - 43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference 2007

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Event date： 2007

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Investigation on Effects of Fuel Injector Geometry on Penetration in Supersonic Combustor

HIRANO Kohshi, KOUCHI Toshinori, KOIKE Shunsuke, IZUMIKAWA Muneo, MATSUO Akiko, TOMIOKA Sadatake, MASUYA Goro

2007

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Event date： 2007

Language：Japanese

Both the wind tunnel experiments and the numerical analyses on helium injections with various injector geometry configurations were performed in order to achieve high penetration and effective mixing between supersonic crossflow and injectant. The stinger shaped injector showed the best penetration performance among all injectors. There was a difference between the experiment and the numerical analysis in evaluation of the injectant concentration. However, the penetration height resulted from the numerical analysis showed good agreement with that from the experiment. It is believed that the reduction of the disturbance of the plume to the crossflow leads to the increment in the penetration.

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超音速流中への直列4孔噴射の貫通特性

小池俊輔, 河内俊憲, 泉川宗男, 富岡定毅, 升谷五郎

燃焼シンポジウム講演論文集 2007

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Event date： 2007

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超音速燃焼器における燃料噴射孔形状が貫通に及ぼす影響の検討

平野昂志, 河内俊憲, 小池俊輔, 泉川宗男, 松尾亜紀子, 富岡定毅, 升谷五郎

日本流体力学会年会講演アブストラクト集 2007

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Event date： 2007

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Evaluation of heat-flux on scramjet engine wall in Mach 6 flight condition

Shuichi Ueda, Masao Takegoshi, Toshinori Kouchi, Fumiei Ono, Toshihito Saito, Muneo Izumikawa

AIAA 57th International Astronautical Congress, IAC 2006 2006

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Event date： 2006

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Heat Flux Prediction for Scramjet Engines

T. Kouchi, T. Mitani, T. Hiraiwa, M. Kodera, G. Masuya

Proceedings of 1st International Conference of Flow Dynamics 2004.11

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Event date： 2004.11

Language：English

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Scramjet performance achieved in engine tests from M4 to M8 flight conditions

Tohru Mitani, Sadatake Tomioka, Takeshi Kanda, Nobuo Chinzei, Toshinori Kouchi

12th AIAA International Space Planes and Hypersonic Systems and Technologies 2003

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Event date： 2003

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超音速流中における噴流の乱流混合のLES解析

第42回流体力学講演会/ 航空宇宙数値シミュレーション技術シンポジウム2010 2010

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エジェクタ・ラムジェットの二次燃料分布

第42回流体力学講演会/ 航空宇宙数値シミュレーション技術シンポジウム2010 2010

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Penetration Characteristics of Pulsed Injection into Supersonic Crossflow

46th AIAA/ASME/SAE/ASEE Joint Propulsion Conference & Exhibit 2010

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高速シュリーレンを用いた超音速噴流場のスペクトル解析

第42回流体力学講演会/ 航空宇宙数値シミュレーション技術シンポジウム2010 2010

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ステレオPIVを用いた超音速流れ場の境界層速度計測

第42回流体力学講演会/ 航空宇宙数値シミュレーション技術シンポジウム2010 2010

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超音速流中における噴流の乱流混合のLES解析

第42回流体力学講演会/ 航空宇宙数値シミュレーション技術シンポジウム2010 2010

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エジェクタ・ラムジェットの二次燃料分布

第42回流体力学講演会/ 航空宇宙数値シミュレーション技術シンポジウム2010 2010

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高速シュリーレンを用いた超音速噴流場のスペクトル解析

第42回流体力学講演会/ 航空宇宙数値シミュレーション技術シンポジウム2010 2010

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ステレオPIVを用いた超音速流れ場の境界層速度計測

第42回流体力学講演会/ 航空宇宙数値シミュレーション技術シンポジウム2010 2010

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Time-space Trajectory of Unsteady Jet into Supersonic Crossflow Using High- Speed Framing Schlieren Images

16th AIAA/DLR/DGLR International Space Planes and Hypersonic Systems and Technologies Conference 2009

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超音速横風中のパルス噴射において観測された噴流貫通のヒステリシス

日本航空宇宙学会北部支部2009年講演会ならびに第10回再使用型宇宙推進系シンポジウム 2009

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超音速流中におけるパルス噴流の貫通特性

第40回流体力学講演会／航空宇宙数値シミュレーション技術シンポジウム 2008 2008

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高速シュリーレン撮影を用いた超音速流中における垂直噴流の貫通の評価

第40回流体力学講演会／航空宇宙数値シミュレーション技術シンポジウム 2008 2008

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Combustion Performance of Supersonic Combustor with Stinger-Shaped Fuel Injector

44th AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2008

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Pulsed Transverse Injection Applied to a Supersonic Flow

43rd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2007

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数値計算による複合エンジンの静止大気中における吸い込み性能予測

第47 回航空原動機・宇宙推進講演会 2007

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超音速流中でのパルス噴射の貫通と混合

日本航空宇宙学会北部支部20周年記念講演会ならびに第8回再使用型宇宙推進系シンポジウム 2007

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数値計算による複合エンジンの静止大気中における吸い込み性能予測

第47 回航空原動機・宇宙推進講演会 2007

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ロケット複合エンジンのエジェクタモードにおける始動特性

日本航空宇宙学会北部支部2006年講演会ならびに第7回再使用型宇宙推進系シンポジウム 2006

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Performance of a RBCC Combustor Operating in Ramjet Mode

42nd AIAA/ASME/SAE/ASEE Joint Propulsion Conference and Exhibit 2006

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Transition of Combustion Modes in a Scramjet Engine

25th International Symposium on Space Technology and Science 2006

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ロケット複合エンジンのエジェクタモードにおける始動特性

日本航空宇宙学会北部支部2006年講演会ならびに第7回再使用型宇宙推進系シンポジウム 2006

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Problems of Numerical Diffusion Found in Scramjets

AIAA/CIRA 13th International Space Planes and Hypersonics Systems and Technologies Conference 2005

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Heat Flux Prediction for Scramjet Engines, - Accuracy of Reynolds Analogy on Scramjet Internal Walls

24th International Symposium on Space Technology and Science 2004

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境界層抽気がスクラムジェット性能に及ぼす影響

日本機械学会流体工学部門講演会 2003

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Numerical Experiments of Scramjet Combustion with Boundary-Layer Bleeding

12th AIAA International Space Planes and Hypersonic Systems and Technologies 2003

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Effects of Reynolds Number on Scramjet Inlet Performance

23rd International Symposium on Space Technology and Science 2002

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レイノルズ数のスクラムジェットインレット性能に及ぼす影響

日本航空宇宙学会北部支部２００２年講演会ならびに第３回再使用型宇宙推進系シンポジウム 2002

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Works

複合エンジンにおける二次燃焼効率向上

2008

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2010

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複合エンジンにおける二次燃焼効率向上

2008

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2010

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推力向上のための混合促進手法の検証

2007

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2008

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推力向上のための混合促進手法の検証

2007

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2008

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Awards

第42回流体力学講演会/航空宇宙数値シミュレーション技術シンポジウム2010 最優秀賞

2010

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東北大学総長賞

2005

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日本航空宇宙学会北部支部 2002 年講演会 Best Presentation Award for Student

2002

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Research Projects

Prediction of Instantaneous wall shear stress distribution through the fusion of Experimental/Computational/Data-driven Fluid Dynamics

Grant number：22K18302 2022.06 - 2025.03

Japan Society for the Promotion of Science Grants-in-Aid for Scientific Research Grant-in-Aid for Challenging Research (Pioneering) Grant-in-Aid for Challenging Research (Pioneering)

河内俊憲, 田中健人

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Grant amount：\25870000 （ Direct expense: \19900000 、 Indirect expense：\5970000 ）

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高レイノルズ数空力予測の精度向上を目指した衝撃波/境界層干渉の先進画像計測

Grant number：22H01684 2022.04 - 2026.03

日本学術振興会科学研究費助成事業基盤研究(B) 基盤研究(B)

河内俊憲, 鈴木博貴, 田中健人

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Grant amount：\17420000 （ Direct expense: \13400000 、 Indirect expense：\4020000 ）

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高レイノルズ数空力予測の精度向上を目指した衝撃波/境界層干渉の先進画像計測

Grant number：23K22954 2022.04 - 2026.03

日本学術振興会科学研究費助成事業基盤研究(B)

河内俊憲, 鈴木博貴, 田中健人

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Grant amount：\17420000 （ Direct expense: \13400000 、 Indirect expense：\4020000 ）

本研究では、レイノルズ数を大きく変化させた条件で、付着境界層や衝撃波-境界層干渉に伴うはく離の詳細なデータを先進画像計測を用いて取得し、これらデータを用いて検証した高忠実な数値計算に機械学習を併用することで、高レイノルズ数流れにおけるはく離の計算モデル構築を目指している。
2023年度、実験としては大きく2つの成果を得た。一つ目は付着境界層の実験を通じた計測システムの改良で、二つ目は斜め衝撃波導入法の確立である。既存のシステムでは本研究での鍵となる流速と壁面せん断応力を同じ位置、また同時刻に計測することは困難であった。後述する斜め衝撃の導入方法の変更と併せて、油膜干渉法にカメラキャリブレーションとミラーを導入することで、これを改善した。斜め衝撃波の導入方法としては、既存の金属製ランプブロックの挿入から3Dプリンター製樹脂ランプのガラス面への接着による方法に変更した。これにより、計測したい任意の位置に容易に任意の強さの斜め衝撃波の導入が可能となった。現状、これら改良したシステムを用いた詳細なデータ取得は出来てないため、2024年度以降、これを行う。実験に対応する数値計算に関しては、衝撃波-境界層干渉の高解像度計算を実施できた。得られた結果を文献値と比較したところ、これまで用いてきたスキームでは、境界層のはく離の状況（圧力変動やはく離長さ）を正確に捉えることが困難であることが分かった。現在、高精度・高忠実、かつ斜め衝撃波を導入する境界条件に対応可能なスキームの開発を行っている。高レイノルズ数流れにおける壁面せん断応力を予測する深層学習モデルの構築に関しては、モデルの入力となる流速分布の高さ方向位置を壁面に近づけることで、ロバスト性が改善すること、また正解データとなる壁面せん断応力値の学習確立を均等にすることで、さらなる精度・ロバスト性の改善が見込めることが分かった。

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Mechanism of Transonic Buffet for A Swept Wing Revealed by Advanced Fluid Measurements

Grant number：18H03814 2018.04 - 2022.03

Japan Society for the Promotion of Science Grants-in-Aid for Scientific Research Grant-in-Aid for Scientific Research (A)

Kouchi Toshinori

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Grant amount：\44200000 （ Direct expense: \34000000 、 Indirect expense：\10200000 ）

We conducted a series of the wind tunnel experiments focused on a shock wave-boundary layer interaction inducing a transonic buffet which determines capability of a flight in a high-speed region. Wing model had a 10°sweep angle and a cross section of NASA common research model, which is a simplified model for a commercial aircraft wing. Through this work, we newly developed a dual layer focusing schlieren system to take flow information with several tens of kHz frame rate. We combined this system with unsteady pressure sensitive paint (uPSP) measurement system which take wall information with several kHz frame rate, to measure the flow-field both around the wing and on the wing surface. We successfully measured flow and wall information for the buffet with high spatiotemporal resolution in being the first in the world. Based on these data, we obtained new knowledge on the generation and maintenance of the self-oscillation of the shock wave for the swept wing.

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Development of Unsteady Velocity Measurement using Afterglow of an Image Intensifier

Grant number：17K18938 2017.06 - 2019.03

Japan Society for the Promotion of Science Grants-in-Aid for Scientific Research Grant-in-Aid for Challenging Research (Exploratory) Grant-in-Aid for Challenging Research (Exploratory)

Kouchi Toshinori

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Grant amount：\6370000 （ Direct expense: \4900000 、 Indirect expense：\1470000 ）

Unsteady velocity measurements in supersonic flows is very challenging topics. I developed new measurement system which is able to measure unsteady velocity using a continuous laser light and an image intensifier. First, I applied the measurement system to low speed wind tunnel experiments to confirm that my new idea is correct or not. The present data well agreed with the previous ones. Therefore, I conclude that my new measurement system has an enough potential to measure unsteady velocity-field. However, the developed system cannot measure the velocity in supersonic flow, because measurement uncertainty became increased compared to that in the low speed experiments. Unfortunately, I cannot improve this within the term of this project. In addition to confirm my idea being correct, I developed new generation method of tracer particle using velocity measurement. This particle has potential to reveal much detail flow structure in highly turbulent flows.

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Two-color PLIF Measurement of Instantaneous Molar Fraction in A Supersonic Combustor

Grant number：15H04199 2015.04 - 2018.03

Japan Society for the Promotion of Science Grants-in-Aid for Scientific Research Grant-in-Aid for Scientific Research (B) Grant-in-Aid for Scientific Research (B)

Kouchi Toshinori

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Grant amount：\16380000 （ Direct expense: \12600000 、 Indirect expense：\3780000 ）

Spaceplane is a promising candidate for next generation space transportation system. Supersonic mixing and combustion are keys to realize the spaceplane. We developed a new technique to measure instantaneous injectant molar fraction in a supersonic flow through this project. The measurement technique is based on Planner Laser Induced Fluoresces (PLIF) using tracer molecules which are excited by laser light. To establish the technique, we first investigated photochemical characteristics of toluene under low-temperature and pressure conditions which is observed in a suction-type supersonic wind tunnel. Then, we established the two-color PLIF measurement system. By using this new measurement system, we are able to quantitatively evaluate mixing efficiency of fuel in a supersonic flow.

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Two-color Fluorescence ratio method to measure instantaneous mole fraction and density in compressible mixing field

Grant number：24656512 2012

Japan Society for the Promotion of Science Grants-in-Aid for Scientific Research Grant-in-Aid for Challenging Exploratory Research Grant-in-Aid for Challenging Exploratory Research

MASUYA Goro, TAKITA Kenichi, KOUCHI Toshinori

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Grant amount：\4030000 （ Direct expense: \3100000 、 Indirect expense：\930000 ）

Fast mixing of fuel and air is one of the most important technical subjects to realize hypersonic air breathing engines. In order to measure instantaneous distribution of fuel mole fraction, we tried to develop a new technique using laser induced fluorescence signals of two tracer gases. We investigated fluorescent characteristics of several candidate matters and selected acetone and toluene as the tracer gas. We tested fluorescent characteristics of their mixture in air and other gases.

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Investigation of Mixing Mechanism in A Scramjet Combustor Using Combined PIV-LIF Measurement System

Grant number：23360377 2011.04 - 2014.03

Japan Society for the Promotion of Science Grants-in-Aid for Scientific Research Grant-in-Aid for Scientific Research (B) Grant-in-Aid for Scientific Research (B)

KOUCHI Toshinori, MASUYA Goro, TAKITA Kenichi, TOMIOKA Sadatake

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Grant amount：\19110000 （ Direct expense: \14700000 、 Indirect expense：\4410000 ）

Scramjet engine is one of the promising candidates as a propulsion system for hypersonic flight vehicles and space planes. We developed a combined stereoscopic Particle Image Velocimetry (PIV) and acetone Planar Laser Induced Fluoresce (PLIF) measurement system, to evaluate turbulent eddy diffusion flux in the combustor, which physically means the averaged transport due to turbulent fluctuations. We applied this measurement system to a transverse jet in a Mach 2 supersonic flow with/without pseudo shock wave, simulating the scramjet combustor. The system successfully measured the eddy flux in the flowfield. These quantitative data provided insight into the fundamental physics of the supersonic mixing.

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平衡／非平衡プラズマの併用による超音速流中での着火・燃焼促進

Grant number：23360375 2011.04 - 2014.03

日本学術振興会科学研究費助成事業基盤研究(B) 基盤研究(B)

滝田謙一, 升谷五郎, 河内俊憲

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Grant amount：\18460000 （ Direct expense: \14200000 、 Indirect expense：\4260000 ）

本研究は，平衡（熱）プラズマと非平衡（低温）プラズマの併用により極めてエネルギ効率の高い着火・燃焼促進技術の新規開発を目的とする。平成24年度は ①平衡／非平衡プラズマを併用した着火システムによる着火・燃焼実験，②プラズマ及び火炎の光学計測，③プラズマ反応のモデリング，④３次元燃焼解析コードを用いたプラズマ着火の数値シミュレーションの実施を計画し，以下の成果を得た。
①については，プラズマジェット（PJ)トーチと誘電体バリア放電（DBD）を併用した着火システムを用いて，水素及び炭化水素を燃料とする着火・燃焼実験を行った。その結果，水素燃料についてはDBD装置の併用による着火促進効果が見られた。しかしスクラムジェットの代表的な炭化水素燃料であるエチレンに対しては，目立った着火促進効果を捉えることができなかった。
②については今年度は実施しなかった。
③については，空気中でDBD装置を作動させた場合に，多く生成されることが知られているオゾンを燃焼機構に加えて着火遅れ時間の解析を行い，上記①で観測されたエチレン燃料に対してDBD装置を併用しても着火促進効果がほとんど見られない原因を探った。
④については水素燃料について，DBD装置の作動を模擬するオゾン添加を行う領域とオゾン添加濃度を変化させた計算を行った。その結果，断面全域に平均的にオゾンを加えた場合と同等の着火促進効果を，噴射孔側の壁面付近に集中的にオゾンを供給することができ，より効率的にオゾンの着火促進効果を得られることを見出した。

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Investigation of Mixing Enhancement Mechanism Caused by Pseudo-Shock Wave

Grant number：20360081 2008 - 2011

Japan Society for the Promotion of Science Grants-in-Aid for Scientific Research Grant-in-Aid for Scientific Research (B) Grant-in-Aid for Scientific Research (B)

MASUYA Goro, TAKITA Kenichi, KOUCHI Toshinori

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Grant type：Competitive

Grant amount：\19890000 （ Direct expense: \15300000 、 Indirect expense：\4590000 ）

Mixing of fuel injected into supersonic internal flow with a pseudo-shock wave, which appears in the combustor of a dual-mode ramjet engine, is significantly and non-isotropically improved. In order to clarify the mechanism of this mixing enhancement, injectant concentration and velocity distributions were measured using a particle image velocimetry (PIV)and a planar laser-induced fluorescence (PLIF), respectively. In addition, numerical simulations were carried out to understand the flowfield. As a result, we found that the pseudo-shock wave produced strong turbulence near the wall and it enhanced mixing of the jet.

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Enhancement of Fuel Mixing and Jet Penetration using Pulsed Injection into a Supersonic Flow

Grant number：20760105 2008 - 2010

Japan Society for the Promotion of Science Grants-in-Aid for Scientific Research Grant-in-Aid for Young Scientists (B) Grant-in-Aid for Young Scientists (B)

KOUCHI Toshinori

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Grant type：Competitive

Grant amount：\4290000 （ Direct expense: \3300000 、 Indirect expense：\990000 ）

This research experimentally and numerically investigated the penetration characteristics of the pulsed injection into Mach 2 supersonic crossflow. This research revealed the pulsed jet penetration in a rising phase of injection pressure was higher than that in a declining phase of injection pressure at a certain value of injection pressure. This hysteresis was owing to the upward flow produced by the pulsed jet like a slug which inclined toward the injection wall. The numerical simulations revealed the vortex rings was generated in each pulse cycle. They dominated the jet penetration and promoted mixing of the injectant with crossflow-air. Based on these experimental and numerical results, we conclude that the pulsed injection could control the jet penetration and mixing by changing its frequency.

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Ignition and Combustion Enhancement by non-equilibrium plasma in supersonic flow

Grant number：20360378 2008 - 2010

Japan Society for the Promotion of Science Grants-in-Aid for Scientific Research Grant-in-Aid for Scientific Research (B) Grant-in-Aid for Scientific Research (B)

TAKITA Kenichi, MASUYA Goro, KOUCHI Toshinori

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Grant amount：\18720000 （ Direct expense: \14400000 、 Indirect expense：\4320000 ）

The generation method of non-equilibrium plasma by dielectric barrier discharge(DBD)in a supersonic flow was established. Excited nitrogen molecules and oxygen radicals, which were suitable for ignition and combustion enhancement, were detected by a spectroscopic measurement. The effects of applied voltage and frequency in discharge on the generation of non-equilibrium plasma were clarified and the electric energy for generation of the plasma was estimated. Moreover, efficient discharge conditions for radical generation were theoretically supposed.

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スクラムジェットエンジン内部形状の最適化

Grant number：03J07299 2003 - 2005

日本学術振興会科学研究費助成事業特別研究員奨励費特別研究員奨励費

河内俊憲

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Grant amount：\1700000 （ Direct expense: \1700000 ）

極超音速飛行するスペースブレーン用のエンジンとして有望視されている,スクラムジェットエンジン内壁におけるレイノルズアナロジーの妥当性を,数値計算を用いて定量的に議論し,その適用限界を調べた.その結果±10%程度の範囲で,エンジン内壁のおよそ90%でレイノルズアナロジーが適用できることが分かった.そこで,このレイノルズアナロジーを組み込んだ一次元解析により,いくつかのエンジン形状と飛行条件について熱負荷や冷却要求を調べた.例えばストラット付きエンジンでは,マッハ8飛行条件において,エンジン平均熱流束は燃焼時に0.5MW/m2となり,冷却に必要な水素流量は,燃焼用の燃料流量と同程度になることが分かった.従って,今後エンジンの作動マッハ数域を広げるには,冷却要請のおよそ80%を占める燃焼器においてフィルム冷却を行ったり,形状を最適化していく必要がある.
マッハ6飛行条件のストラット付きスクラムジェットエンジンと,そのエンジンの燃焼器の一部を切り出したセクター燃焼器モデルに対して反応流計算を行い,エンジン内の火炎形状が,燃焼性能をどのように決定しているのか,またインレットの偏流が燃焼性能に対してどのような影響を与えているかを考察した.その結果,インレットの偏流により,燃料の大規模な合体が生じ,燃焼効率の増加が著しく抑制されていることが分かった.従って,今後エンジン性能を改善していくには,燃料噴流の合体を防ぐために,燃料噴射孔間隔の最適化を図ること,特にインレットを最適化し,カウル衝撃波による境界層内の二次流を低減していく必要がある.また数値計算で得られた,エンジン内の火炎構造と燃焼効率分布を比較することで,供試エンジンでも,ストラット壁側からの垂直噴射,ストラットベース面・カウル側からの平行噴射を行えば、燃焼性能を改善しうることが分かった.

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Vector and Complex Analyses （2024academic year） Second semester - 月3～4,木1～2
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岡山大学公開講座岡山大学先端研究講座航空機の翼に関する空気力学

Role(s)：Lecturer

2022.12.17

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File： oukouza2022.pdf

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発見！アドレナ人岡山大学（河内研究室） TV or radio program

テレビ新広島 2022.6.29

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