Updated on 2022/09/24

写真a

 
KOUCHI Toshinori
 
Organization
Faculty of Natural Science and Technology Professor
Position
Professor
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

Committee Memberships

  • 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   

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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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  • 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

  • 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

    2022.1

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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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    Language:English   Publishing type:Research paper (scientific journal)   Publisher:American Institute of Aeronautics and Astronautics (AIAA)  

    DOI: 10.2514/1.b37683

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  • Influence of Partial Electrical Conducting Wall on Electrodynamic Flow Control Reviewed

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

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

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    Language:English   Publishing type:Research paper (scientific journal)   Publisher:Japan Society for Aeronautical and Space Sciences  

    DOI: 10.2322/tastj.19.68

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

    DOI: 10.2514/6.2020-1335

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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   AIAA 2020-2040   2020

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    © 2020, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. Turbulence grids were applied to Mach 2 supersonic wind tunnel to increase turbulence in a mainstream. We measured wall pressure, velocity by Laser Speckle Velocimetry (LSV) using acetone condensation nanoparticle and density by acetone Planer Laser Induced Fluorescence (PLIF). In this study, the test section has 12 mm width and 10 mm height at the exit of the nozzle and the turbulence grids, which consisted of tungsten wires having sub-mm diameter, was installed at the exit of the nozzle. Combination of the wire grid and tunnel wall expansion increased mainstream turbulence without flow unstart in the test section flow. In the case with 0.4-mm-diameter grid at 3 by 3 arrangement having a blockage of 21% of the nozzle exit area, the mainstream turbulence reached 8% of the mainstream velocity. Nitrogen gas was perpendicularly injected into the grid-generated supersonic turbulent flow and it mixing performance was investigated by using acetone-PLIF. Installation of the wire grid affected not only mainstream turbulence but also wall-bounded flow, resulting in thickening boundary layer. As a result, jet penetration increased with installing the wire grid. However, no remarkable improvement of the jet mixing was observed with installing the wire grid.

    DOI: 10.2514/6.2020-2040

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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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    Publishing type:Research paper (scientific journal)   Publisher:Scientific Research Publishing, Inc.  

    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   032001 - 032001   2019.3

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

    DOI: 10.1088/1755-1315/240/3/032001

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    Other Link: http://stacks.iop.org/1755-1315/240/i=3/a=032001?key=crossref.08f776deeae50d29012044336078de89

  • Hydrodynamic Instability with Convective Heat Transfer through a Curved Channel with Strong Rotational Speed

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

    8TH BSME INTERNATIONAL CONFERENCE ON THERMAL ENGINEERING   2121   2019

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    Language:English   Publishing type:Research paper (international conference proceedings)   Publisher:AMER INST PHYSICS  

    In this paper, a comprehensive numerical study on viscous incompressible fluid flow and heat transfer through a loosely coiled square duct has been presented. Spectral method is used as a basic tool to solve the system of non-linear partial differential equations. Numerical calculations are carried out for the Dean number Dn = 1000 with a temperature difference across the vertical sidewalls for the Grashof number Gr = 100, where the outer wall is heated and the inner wall cooled. A rotation of the duct about the center of curvature is imposed in the positive direction for the Taylor number 0 <= Tr <= 2000 and combined effects of the centrifugal, Coriolis and buoyancy forces are investigated. First, steady solutions are obtained by the Newton-Raphson iteration method. As a result, three branches of asymmetric steady solutions with two- to four-vortex solutions are obtained. Then, time evolution calculations as well as power spectrum density of the unsteady solutions are obtained and it is found that the unsteady flow undergoes through various flow instabilities, if Tr is increased in the positive direction. Nusselt numbers are calculated as an index of convective heat transfer, and it is found that convective heat transfer is significantly enhanced by the secondary flow. Finally, a comparison between the numerical and experimental investigations has been provided. It is found that there is a good agreement between the numerical and experimental investigations.

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

    © 2019, American Institute of Aeronautics and Astronautics Inc, AIAA. All rights reserved. Condensation nanoparticle planar laser light scattering imaging was conducted in a suction type Mach 1.9 supersonic flow. A series of the nanoparticle image pair was obtained by using the same optical components of PIV. The velocity data were obtained by the image pairs using the image-based correlation procedure as same as PIV. Acetone vapor instead of tracer particles in a conventional PIV was added to a mainstream gas in a reservoir. Acceleration process through a Laval nozzle automatically generated condensation particles of the acetone which were uniformly seeded into the entire flowfield. The increase in the additive concentration increased the number density of the particle and enabled a detail visualization of the vortex structures in the boundary layer. The increase in the additive concentration also increased the mean molecular weight of the acetone-seeded air. This decreased the flow speed. However, this is not a big matter because the heat release due to the condensation was negligible and the decrease in the flow speed was easily predicted from the thermodynamic properties of the gas. The particle size was difficult to be measured directly, so the tracer response time was estimated by the oblique shock test. The Stokes diameter of the particle was estimated to be 160 nm. Such a small diameter particle provides high traceability resulting in capturing shock wave with a few vector spacing and also provides high spatial resolution image resulting in capturing sub-mm scale vortices within the boundary layer. The mean and turbulent velocity fields evaluated from such high spatially and temporally resolved image pairs fairly agreed with previous measurement in the boundary layer.

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

    <p>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. </p>

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

    Turbulent flow through helical pipes with circular cross section is numerically investigated comparing with the experimental results obtained by our team. Numerical calculations are carried out for two helical circular pipes having different pitches and the same nondimensional curvature δ (=0.1) over a wide range of the Reynolds number from 3000 to 21,000 for torsion parameter β (=torsion /2δ  = 0.02 and 0.45). We numerically obtained the secondary flow, the axial flow and the intensity of the turbulent kinetic energy by use of three turbulence models incorporated in OpenFOAM. We found that the change to fully developed turbulence is identified by comparing experimental data with the results of numerical simulations using turbulence models. We also found that renormalization group (RNG) k−ε turbulence model can predict excellently the fully developed turbulent flow with comparison to the experimental data. It is found that the momentum transfer due to turbulence dominates the secondary flow pattern of the turbulent helical pipe flow. It is interesting that torsion effect is more remarkable for turbulent flows than laminar flows.

    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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    Authorship:Lead author   Language:English   Publishing type:Research paper (scientific journal)   Publisher:Springer Science and Business Media LLC  

    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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    Three-dimensional direct numerical simulations of a viscous incompressible fluid flow through a helical pipe with a circular cross section were conducted for three Reynolds numbers, <italic>Re</italic>(= 80, 300, and 1000), and two nondimensional curvatures, δ (= 0.1 and 0.05), over a wide range of torsion parameters, β (= nondimensional torsion/<inline-formula><tex-math version="MathJax"><![CDATA[\(\sqrt{2\delta } \)]]></tex-math></inline-formula>), from 0.02 to 2.8. Well-developed axially invariant regions were obtained where the friction factors were calculated, in good agreement with the experimental data obtained by Yamamoto et al. [<ext-link ext-link-type="uri" xlink:href="https://doi.org/10.1016/0169-5983(95)00022-6" xlink:type="simple">Fluid Dyn. Res. <bold>16</bold>, 237 (1995)</ext-link>]. It was found that the friction factor sharply increases as β increases from zero, then decreases after taking a maximum, and finally slowly approaches that of a straight pipe when β tends to infinity. It is interesting that a peak of the friction factor exists in the region 0.2 ≤ β ≤ 0.3 for all the Reynolds numbers and curvatures studied in the present paper, which manifests the importance of the torsion parameter in helical pipe flow.

    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  

    <p>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.</p>

    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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    Authorship:Lead author   Language:English   Publishing type:Research paper (scientific journal)   Publisher:Japan Society for Aeronautical and Space Sciences  

    DOI: 10.2322/tjsass.60.56

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

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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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    Authorship:Lead author   Language:Japanese   Publisher:Japan Society of Mechanical Engineers  

    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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  • 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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    Authorship:Lead author   Language:English   Publishing type:Research paper (scientific journal)   Publisher:Springer Science and Business Media LLC  

    We visualized the shock buffets on a two-dimensional transonic airfoil with and without vortex generators (VGs) by using a fast-framing focusing schlieren imaging. The focusing schlieren visualization showed that the flow three-dimensionality around the airfoil became remarkable with installing the VGs. This implies that narrow depth of focus of imaging systems was a key to accurately capture the characteristics of the shock oscillation due to the buffet for the cases with VGs. The time-resolved imaging also revealed that non-periodic components were included in the shock oscillation due to the buffet for the cases with VGs. This prevented Fourier analysis from being applied. We used wavelet analysis to extract the characteristic of the shock oscillation for the cases with VGs. The wavelet spectrograms revealed that the low-frequency oscillation having the buffet frequency was still included intermittently in the shock oscillation even when VG controlled the buffet. The rate of appearing the low-frequency oscillation increased with increasing both the interval between VGs and the angle of attack.

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

    DOI: 10.1252/jcej.15we099

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

    © 2016, American Institute of Aeronautics and Astronautics Inc, AIAA. All Rights Reserved. An experiment to investigate the effect of pseudo-shock wave (PSW) on turbulent diffusion of a transverse jet in a Mach 2.0 supersonic crossflow was conducted. The vertical jet from a 2.5 mm-diameter orifice was injected into pseudo-shock wave and jetto-crossflow momentum flux ratio was 2.2. To measure turbulent diffusion flux, stereoscopic particle image velocimetry (SPIV) and acetone planar laser-induced fluorescence (PLIF) system were combined and velocity and concentration fields were simultaneously measured. Measurement plane was a cross section at 10 mm downstream from the injection port. The position of PSW was controlled by a flow plug at the duct exit driven by a stepping motor. The front of PSW was set at 30 mm upstream from the orifice. Without PSW, turbulent diffusion flux (TDF) of the injectant was extended upward and the shape of injectant plume was deformed by a counter-rotating vortex pair (CVP) which was formed behind the injected gas. Under PSW, the CVP made horseshoe-shape concentration distribution. TDF directed from spur of concentration to both free stream side and lee side of the jet. Most of no-PSW condition and outward of under-PSW TDF was concentration-fluctuation-dominant, only inward TDF under PSW emerged as turbulent-dominant. The effect of PSW that enhances diffusion of injected gas was confirmed.

    DOI: 10.2514/6.2016-0662

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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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    Authorship:Corresponding author   Language:Japanese   Publisher:Japan Society for Aeronautical and Space Sciences  

    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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    Authorship:Lead author   Language:English   Publishing type:Research paper (scientific journal)   Publisher:Springer Science and Business Media LLC  

    DOI: 10.1007/s00348-015-2081-9

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    Other Link: http://link.springer.com/article/10.1007/s00348-015-2081-9/fulltext.html

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

    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&times;106. Angle of attack without corrections (&alpha;) was changed from 4&deg; to 6&deg;. The present focusing schlieren system had &plusmn;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 20&mu;s exposure time. The present imaging system well captured the shock wave motion on the airfoil. At &alpha; = 4&deg;, the shock wave was positioned at x/c&sim;0.45. The shock wave was slightly fluctuated with a frequency of 585.5Hz. Above &alpha; = 5&deg;, the wing buffet occurred. The buffet frequency increased as increasing &alpha;. 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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  • Collaborative Experimental and Computational Study of a Dual-Mode Scramjet Combustor Reviewed

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

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

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

    Junya Watanabe, Toshinori Kouchi, Kenichi Takita, Goro Masuya

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

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  • Supersonic Combustion Using a Stinger-Shaped Fuel Injector Reviewed

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

    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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    The effects of injectant species on the turbulent structure and mixing state of jets in supersonic crossflow were investigated using a large-eddy simulation. Hydrogen, helium, nitrogen, and ethylene were transversely injected into a Mach 1.9 airflow at a constant jet-to-crossflow momentum flux ratio. The time-averaged distribution of jet concentration was roughly the same for all the injectant species, but the large-scale structure of scalar fluctuation differed significantly. The probability density functions of injectant mass fraction revealed that the turbulent behavior of nitrogen and ethylene jets was highly intermittent. The velocity field was considerably different between the injectants, owing to the different injection velocities. The hydrogen and helium jets had a much higher velocity difference between jet and crossflow in the near field; thus, the observed turbulent intensities for these two injectants were much higher than those for nitrogen and ethylene. In addition, the spectral analysis of velocity fluctuations in the windward mixing layer showed that the scale of energetic eddies was larger in the hydrogen and helium jets than in the nitrogen and ethylene jets. These characteristics resulted in better mixing in the hydrogen jet than in the ethylene jet for the studied injection conditions.

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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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    We performed an experimental investigation of the flowfield of a transverse jet into supersonic flow with a pseudo-shock wave (PSW). In this study, we injected compressed air as the injectant, simulating hydrocarbon fuel. A back pressure control valve generated PSW into Mach 2. 5 supersonic flow and controlled its position. The positions of PSW were set at nondimensional distance from the injector by the duct height (x/H) of -1. 0, -2. 5, and -4. 0. Particle image velocimetry (PIV) gave us the velocity of the flowfield. Mie scattering of oil mist only with the jet was used to measure the spread of the injectant. Furthermore, gas sampling measurements at the exit of the test section were carried out to determine the injectant mole fraction distributions. Gas sampling data qualitatively matched the intensity of Mie scattering. PIV measurements indicated that far-upstream PSW decelerated the flow speed of the main stream and developed the boundary layer on the wall of the test section. The flow speed deceleration at the corner of the test section was remarkable. The PSW produced nonuniformity in the main stream and reduced the momentum flux of the main stream in front of the injector. The blowing ratio, defined as the square root of the momentum flux ratio, of the jet and the main stream considering the effect of the boundary layer thickness was shown to be a useful parameter to explain the jet behavior. © 2012 Springer-Verlag.

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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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    The mean and turbulent velocity field of a transverse jet in a supersonic flow with a pseudo shock wave by stereoscopic particle image velocimetry was measured. Both the mainstream and the injectant were unheated air. The pseudo shock wave was generated and controlled by means of a flow plug driven by a stepping motor. To study the influence of the generation and development of the pseudo shock wave, measurements are taken for four different cases of the pseudo shock wave location, including one without a pseudo shock wave. Sequences of up to 750 image pairs for each measurement plane were acquired. From these data, the mean and turbulent characteristics of the flowfield were examined, such as mean velocity and vorticity, turbulence intensities, Reynolds stresses, and turbulence kinetic energy. The mean velocity and vorticity indicate that the pseudo shock wave gradually lowered the flow speed of the mainstream and increased the size of the counter-rotating vortex pair. The pseudo shock wave strongly disturbed the flowfield, inducing complicated three-dimensional distortions. The pseudo shock wave disturbed the flowfields near the walls, and the turbulence kinetic energy in this area was kept at a high level over long streamwise distances. The streamwise fluctuation intensity was about 4 times stronger than that of the vertical and lateral components, and the streamwise velocity components fluctuated even more greatly than the cross-sectional velocity components. The transverse injection moderately affected not only turbulence around the jet, but also the turbulent characteristics caused by the pseudo shock wave. The injection not only produced turbulence around the jet, but also suppressed the velocity fluctuation caused by the pseudo shock wave.

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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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    Nonreacting experiments were conducted at Mach 2 to understand the relationship between a wall-mounted alternating-ramp-wedge-type hypermixer and transverse injection compared with a step mixer. Experimental techniques such as schlieren visualization and stereoscopic particle image velocimetry were employed to study the three-dimensional flowfield with vortex structures induced by the interaction between the mixer and transverse injection. Without injection, the hypermixer creates a region that contains vortical motions. When a transverse jet is injected in the vortical region, flow parameters on mixing performance, such as the penetration height, vorticity, and turbulent stress, are improved. Three turbulent-stress components show relatively distinct distributions, and strong turbulent stresses are observed at the upper side of the jet plume. Turbulent-stress distributions are significantly associated with strain rate, which peaks along the sonic line of the jet plume.

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

    Toshinori Kouchi, Goro Masuya, Tohru Mitani, Sadatake Tomioka

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

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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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    A three-flow-tube, quasi-one dimentional calculation was carried out to estimate modetransition fuel equivalence ratios under clean and vitiated inflow conditions. A simple flame holding model was used in the calculation. In cases of vitiated inflows, both total temperature and total enthalpy matched conditions to that of clean air were tested. Calculated wall pressure distributions were well matched to those of experimental values, qualitatively. Additionally, the ratio of mode-transition equivalence ratio of clean inflow divided by that of vitiated inflow was well matched to that of experimental value. Matched total enthalpy was effective to eliminate the inflow vitiation effects on mode-transition equivalence ratios in a case that thermal choking was attained at constant area exit. However, in a case that thermal choking was attained in the diverging region, matched total enthalpy was not effective. © 2012 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

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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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    We proposed a new method to evaluate simultaneously both convective velocity and scale of dominant turbulent structures captured in a high speed framing schlieren movie. We took 90 time-series schlieren images of a transverse jet into a Mach 2 supersonic flow with 1 MHz sampling. We focused on periodical image gradations due to the turbulent structures within the jet and boundary layer. We remapped the image intensities on the structures along their trajectory as a time-space map. The time-space map showed swept stripe patterns. The presence of the stripe patterns indicates stable structures were periodically generated and convected downstream. Slope of the stripes corresponds to the convective velocities of the structures. Cycles in the space- and time-directions of the stripes correspond to the scale and formation cycle of the dominant structure. Two-dimensional Fourier transform efficiently extracted the dominant ones from the time-space map. We demonstrated this newlyproposed method using two-dimensional Fourier transform accurately evaluated the convective velocity and scale of the dominant turbulent structures within the jet and boundary layer. © 2012 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

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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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    Schlieren imaging has high sensitivity for density gradient in a flow field, and easily captures not only shock and expansion waves but also turbulent structures in the flow field. The conventional schlieren imaging, however, cannot capture clearly them in directconnect supersonic combustor tests with long duration, because the severe temperature condition in the combustor locally changes the refractive index of the window glasses for optical access. The conventional schlieren technique is essentially sensitive to the entire region of the light path including the glasses. On the other hand, focusing-schlieren technique has narrow depth of focus. Therefore, the imaging is expected to avoid the thermal distortion of the glasses. In this work, we applied focusing-schlieren imaging to the supersonic combustion tests, and tried to clearly capture the flow features inside a dualmode scramjet. The present system had about ± 5 mm depth of focus, and successfully visualized the flow field in the combustor, though the system sensitivity declined with the tunnel heating up. Combustion drastically changed the flow field inside the combustor, and induced volumetric expansion of fuel jet, resulting in pressure rise. Combustiongenerated pressure rise pushed up the shock train up to the trilling edge of the ramp fuel injector. The system recorded two image pairs by using PIV system. These image pairs yielded the convection velocity of turbulent structures in the combustor. © 2012 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

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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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    Numerical simulations of reacting and non-reacting flows within a scramjet combustor configuration experimentally mapped at the University of Virginia's Scramjet Combustion Facility (operating with Configuration "A") are described in this paper. Reynolds-Averaged Navier-Stokes (RANS) and hybrid Large Eddy Simulation /Reynolds-Averaged Navier-Stokes (LES /RANS) methods are utilized, with the intent of comparing essentially 'blind' predictions with results from non-intrusive flow-field measurement methods including coherent anti-Stokes Raman spectroscopy (CARS), hydroxyl radical planar laser-induced fluorescence (OH-PLIF), stereoscopic particle image velocimetry (SPIV), wavelength modulation spectroscopy (WMS), and focusing Schlieren. NC State's REACTMB solver was used both for RANS and LES /RANS, along with a 9-species, 19-reaction H2-air kinetics mechanism by Jachimowski. Inviscid fluxes were evaluated using Edwards' LDFSS flux-splitting scheme, and the Menter BSL turbulence model was utilized in both full-domain RANS simulations and as the unsteady RANS portion of the LES /RANS closure. Simulations were executed and compared with experiment at two equivalence ratios, pdbl= 0.17 and pdbl= 0.34. Results show that the pdbl = 0.17 flame is hotter near the injector while the pdbl = 0.34 flame is displaced further downstream in the combustor, though it is still anchored to the injector. Reactant mixing was predicted to be much better at the lower equivalence ratio. The LES /RANS model appears to predict lower overall heat release compared to RANS (at least for pdbl = 0.17), and its capability to capture the direct effects of larger turbulent eddies leads to much better predictions of reactant mixing and combustion in the flame stabilization region downstream of the fuel injector. Numerical results from the LES/RANS model also show very good agreement with OH-PLIF and SPIV measurements. An un-damped long-wave oscillation of the pre-combustion shock train, which caused convergence problems in some RANS simulations, was also captured in LES /RANS simulations, which were able to accommodate its effects accurately. Copyright © 2012 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

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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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    A Mach 2 hydrogen - air supersonic combustor model with no diffuser was designed and operated in atmospheric inflow condition. A new supersonic mixer, which was vent slot mixer (VSM), was developed and fabricated to use as the device of the fuel-air mixing. At low enthalpy inflow condition, a plasma jet torch was used as the igniter and the flame-holder. An isolator was located between the nozzle and the combustor. In supersonic combustion, the VSM had an effect to increase the mixing efficiency compared with the step mixer. While the combustion pressure was increased, the combustion mode was changed from unstable supersonic combustion to dual-mode transition. When the unstable flow of shock train affected the combustor inlet, the VSM was showed that the combustion stability was slightly sustained when compared with the case ofthe step mixer.

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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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    Large-eddy simulation (LES) of Pseudo-Shock Wave (PSW) in a square duct was perfomed to study the three-dimensional turbulent structure. A flow with the PSW in the square section duct produced by the high back pressure was reproduced using LES. The inflow Mach number was 2.5 and the inflow boundary layer of 4.2mm thick. The incoming boundary layer for a square duct was established using the multi rescaling method. The Mach number distribution, schlieren image, wall pressure, and velocity data obtained from the LES were compared with the past experimental data. The shock train structure observed in the experiment was well reproduced by the LES. The averaged wall pressure and streamwise velocity distributions agreed well between the LES and the experiments. Also, the distributions of intensity and spatial correlation of velocity fluctuation reasonably agreed between the LES and the experiment, although some differences were observed in the velocity fluctuation intensity distribution at the position of front shock wave. © 2012 by the American Institute of Aeronautics and Astronautics, Inc.

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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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    Three-component velocity distributions in a rocket-ramjet combined cycle engine model operating under a sea-level static condition were measured with a stereoscopic particle image velocimetry. The engine model had two rocket nozzles on top wall side of a flow-path and fuel injectors for the secondary combustion. The rocket exhaust was simulated by the cold compressed air injected at operation condition of 2.4 MPa in chamber pressure. The secondary fuel was simulated by the helium gas. The pressure rise due to combustion was simulated by contracting the exit area of flow path by using a flow plug. The separation region appeared in the cowl side in the ensemble-averaged velocity distribution in the case of combustion simulation. The flow around the separation region was strongly disturbed. © 2012 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

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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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    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.

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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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    The three-dimensional turbulent structure and mixing state of a transverse air jet injected into a Mach 1.9 supersonic crossflow were investigated using a large-eddy simulation. Both a grid sensitivity study and detailed comparisons with acetone planar laser-induced fluorescence data were conducted. The large-eddy simulation results well reproduced both the distribution of averaged injectant concentration and the large-scale turbulent features in the windward region of the jet plume. Large-scale vortices on the windward side of the jet plume caused large protrusions of injectant and were the main cause of the turbulent diffusion of injectant toward the crossflow in the near field. The windward large-scale vortex structure consisted of a string of hairpinlike vortices meandering along the jet trajectory. The head of these hairpin vortices tilted toward the upstream and upward directions. The instantaneous combustible injectant mass flux was evaluated by assuming the injectant air to be ethylene. A large amount of combustible injectant existed inside the large-scale protrusions induced by the windward large-scale vortex structure. The combustible injectant mass flow rate passing through the cross section bad substantial fluctuations over time, mainly due to the intermittent appearance of the windward large-scale vortices.

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

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

    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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    A reacting-experiment was conducted to understand the relation between a wallmounted alternating-ramp-wedge type hyper mixer and various injection locations in unheated supersonic flow. The hydrogen gas and a plasma jet torch were used as the fuel and the igniter, respectively. The parallel injection method shows the maximum combustion efficiency for the forced ignition. This is because the fuel-air mixture can be ignited in the heat source (plasma jet) and providing the fuel-air mixture to the plasma jet, i.e., the parallel injection, is very effective to enhance the combustion efficiency. In the cold main flow, the combustion region is restrained and affected by the location of the plasma jet. © 2011 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

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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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    Turbulent structure and mixing state of hydrogen and ethylene jets transversely injected into Mach 1.9 supersonic crossflow was numerically investigated using large-eddy simulation. The feature of windward large-scale structure was largely different between the hydrogen and ethylene jets. The ethylene jet had a highly intermittent feature with intensive geometric change of jet plume. The hydrogen jet had much larger velocity difference between the jet and the crossflow in the near-field, thus much higher turbulent intensity was obtained than in the ethylene jet. In addition, the scale of energetic eddy of hydrogen jet was larger in the windward mixing layer. These probably result in the better mixing in the hydrogen jet than in the ethylene jet. © 2011 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

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  • Flowfield characteristics on a vent slot mixer in supersonic flow Reviewed

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

    Shock Waves   20 ( 6 )   559 - 569   2010.12

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    DOI: 10.1007/s00193-010-0280-0

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  • 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 &amp; Exhibit   2010.7

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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 &amp; 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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    Single-time two-point spatial correlations of injectant concentrations in the supersonic mixing flowfield produced by a sonic transverse injection of air into a Mach 2.0 supersonic airstream were investigated using acetone planar laser-induced fluorescence data. Side-view and end-view contour maps were obtained in several planes to characterize the turbulent structure and three-dimensionality of the mixing flowfield. The correlation maps indicated an organized large-scale structure in the upper region of the jet. The side-view correlation maps revealed that the shape of the large dominating structure was elliptic and that its major axis turned from backward-leaning to forward-leaning as the reference point of correlation moved downstream. The end-view correlation maps showed that the instantaneous jet plume appeared by turns either in the top or in the lower sides of the time-averaged injectant plume in each cross section. Copyright © 2009 by the American Institute of Aeronautics and Astronautics, Inc.

    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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    DOI: 10.2514/6.2009-7316

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  • Supersonic Combustion with Supersonic Injection Through Diamond-Shaped Orifices Reviewed

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

    45th AIAA/ASME/SAE/ASEE Joint Propulsion Conference &amp; Exhibit   27 ( 6 )   1196 - 1203   2009.8

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    DOI: 10.2514/6.2009-5229

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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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    DOI: 10.2514/6.2009-25

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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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  • 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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    DOI: 10.1007/978-3-540-85181-3_54

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  • Design and Experimental Verification of Two Dimensional Asymmetric Supersonic Nozzle Reviewed

    Chae-hyoung Kim, Kunmin Sung, In-Seuck Jeung, Byoungil Choi, Toshinori Kouchi, Goro Masuya

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

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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 &amp; 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

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

    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 &amp; 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 &amp; 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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  • 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 &amp; Exhibit   2006.7

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    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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    Space transportation system uses the liquid hydrogen of the fuel as a coolant of the engine. Therefore, it is necessary to predict the heat flux to the engine wall in high accuracy for efficient cooling with a minimum coolant. However, the prediction of the heat flux to the scramjet engine combustor walls, is quite difficult due to complex interaction of flow and combustion. In this study, a sidewall-compression-type scramjet engine was tested under Mach 6 flight conditions using Ramjet Engine Test Facility. The heat flux was measured using water-cooled heat-flux meters installed on the sidewall within the combustor sections. The experimental results were compared with CFD analysis of the whole engine to predict heat flux distribution on the engine wall. The numerical results of wall pressure distribution showed good agreement with the experimental data. However, the experimental results of heat flux were extremely higher than the numerical results due to the radiation heating which was not considered in the CFD analysis. Based on the results, the average heat flux of the sub-scale scramjet engine with 300 K isothermal walls was 1 MW/m2 in the stoichiometric fuel rate at Mach 6 flight conditions.

    DOI: 10.2514/6.iac-06-c4.5.04

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

    Tohru Mitani, Toshinori Kouchi

    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

    Toshinori Kouchi, Tohru Mitani, Goro Masuya

    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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    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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  • 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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    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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MISC

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

    SANSICA Andrea, HASHIMOTO Atsushi, KOIKE Shunsuke, KOCHI Toshinori

    ( 20 )   109 - 118   2021.2

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    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

  • 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   2021

  • Mean Velocity Measurements of Turbulent Boundary Layer at Reθ=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)   53rd-39th   2021

  • 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

  • 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

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

    河内俊憲, 青山翼, 永田靖典, 柳瀬眞一郎

    日本機械学会中国四国支部総会・講演会講演論文集(CD-ROM)   58th   2020

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

    橋本知幸, 河内俊憲, 永田靖典, 柳瀬眞一郎, 青木礼

    日本機械学会中国四国支部総会・講演会講演論文集(CD-ROM)   58th   2020

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

    志水大知, 永田靖典, 河内俊憲, 柳瀬眞一郎, 乗井拓己

    日本機械学会中国四国支部総会・講演会講演論文集(CD-ROM)   58th   2020

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

    河内俊憲, 山根映介, 柳瀬眞一郎, 永田靖典, 保田和則

    日本機械学会中国四国支部総会・講演会講演論文集(CD-ROM)   58th   2020

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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   2004

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    DOI: 10.2514/6.2003-7009

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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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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

  • 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  

    <p>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.</p>

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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  

    <p>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.</p>

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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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  • 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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  • 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  

    © 2016, American Institute of Aeronautics and Astronautics Inc, AIAA, All rights reserved. We visualized the shock wave-boundary layer interaction on a two-dimensional transonic airfoil with and without vortex generators (VGs) by using a fast-framing focusing schlieren imaging. Image processing extracted a time-space trajectory of the shock wave motion from a time-series of the schlieren images. The shock trajectories were analyzed by using the Morlet wavelet. The shock motions in the cases without VGs were quite periodic. The Fourier analysis well extracted the characteristics of the shock motion such as frequency etc. However, the shock motions in the cases with VGs were not periodic. Therefore, the Fourier analysis is not applicable for this case. The wavelet analysis with the statistical significance test gave quantitative measure of change in the shock oscillation around the buffet frequency due to installation of VGs, such as amplitude and intermittency. The wavelet spectrograms revealed that the installation of VGs did not prevent from generating the buffet but just reduced the amplitude of the buffet oscillation.

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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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  • 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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  • 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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  • 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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  • 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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  • 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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  • 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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  • 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

    Supersonic transverse jet flow-field has an important role for supersonic combustor in scramjet engines. Supersonic speed induces the difficulty in unsteady measurements, because characteristics time is very short in the flow. Lacks of time-series data make the combustor difficult to develop. To investigate the jet unsteady motion, high-speed framing camera captured 100 successive schlieren images of the supersonic transverse jet flow-field with 250 kHz sampling rate. The mainstream Mach number was 2.0 and the injectant was helium gas, simulating fuel hydrogen. This work revealed the effects of density-weighted jetto-crossflow velocity ratio (blowing ratio: r) and the injector diameter (D) on the motion of the jet boundary. Newly suggested image processing, based on the Sobel spatial filter, efficiently tracked the jet boundary from the time-series schlieren images. 2700 sample data gave the probability density function (PDF) of the jet boundary. The PDF distributions indicated the jet penetration was insensitive to both r and D in rD space. The jet spreading, however, was sensitive to both r and D even in rD space. This was due the compressibility effect generated at the near field of injector. Remapping the time-series jet boundary as the time-space jet trajectory indicated the convective velocity of the large eddies in the jet was insensitive to r and D. It was constant of 460 m/s. The map gave us another important information on the jet motion: cycle of high-penetrated eddy formation in the jet. Spectrum analysis of the time-space jet trajectory investigated the shedding frequencies of highpenetrated eddy in the transverse jet. As the results, we find out that the high-penetrated eddy occurred at comparatively various frequencies. The specific amplified frequency of the jet instability probably did not exist at the far field of supersonic transverse injection. Copyright © 2009 by the American Institute of Aeronautics and Astronautics, Inc.

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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

    An experiment was conducted to investigate the mixing mechanism of a jet injected perpendicularly into a mainstream with a pseudo-shock wave (PSW). The velocity fields in the cross-sectional plane were obtained by particle-image velocimetry (PIV). Mixing of the injectant was observed by Mie scattering light of oil mist seeded in the injectant. The PSW thickened the boundary layer and reduced the momentum flux of the mainstream so the injectant penetrate higher from the wall. This affected the injectant mixing. The rd-scale model was applicable to estimate the injectant mixing in PSW by considering the flow condition just upstream of the injection jet. Copyright © 2009 by the American Institute of Aeronautics and Astronautics, Inc.

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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

    Scalar spatial correlations in the supersonic mixing flowfield produced by a sonic transverse injection of air into a Mach 2.0 supersonic airstream were investigated using acetone planar laser-induced fluorescence (acetone PLIF) data. Side-view and end-view images were obtained in several planes to characterize the turbulent structure and three-dimensionality of the mixing flowfield. Single-time two-point spatial correlations of injectant concentration were obtained from the acetone PLIF data. Contour maps of the correlations indicated an organized large-scale structure in the upper region of the jet. Side-view correlation maps revealed that the shape of the large dominating structure was elliptic, and that its major axis turned from backward-leaning to forward-leaning as the reference point of correlation moved downstream. End-view correlation maps revealed that the instantaneous jet plume appeared by turns either in the top or in the lower sides of the timeaveraged injectant plume in each cross-section. Copyright © 2009 by the American Institute of Aeronautics and Astronautics, Inc.

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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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  • 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

    Supersonic combustor with single "stinger-shaped" injector or multi ones arranged side-by-side in the spanwise direction were tested in a direct-connect wind-tunnel facility at a Mach 2.5 with a stagnation condition of 1.05 MPa and 2060 K. The stinger-shaped injector, having sharp leading edge followed by a streamwise slit, produced higher jet penetration in the height-wise direction as compared with the circular injector case at low jet dynamic pressure regime in our previous cold flow tests. In the combustion test, the single stinger-shaped injector produced higher jet penetration, resulting in 10 % higher thrust than the circular case when combustion region was limited in the diverging-area combustor. This injector also provided higher thrust even when flame was anchored around the injector with increasing fuel equivalence ratio (i.e. jet dynamic pressure), though the penetration reduced. This was because the stinger-shaped injector had better flame-holding performance near the injector. In the multi injector case, even with the stinger-shaped injector, the plume growing in the vertical direction, the adjacent fuel jets merged and the large plume was formed. The advantage of the stinger shape was diminished. The thrust performance in the stinger case, however, remained higher than that in the circular case. © 2008 by the American Institute of Aeronautics and Astronautics, Inc.

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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

    An experimental investigation was conducted to reveal jet penetration and mixing performance of pulsed injection in a Mach 2.5 crossflow. Helium and nitrogen gas were injected perpendicularly through flush-mounted circular sonic orifice. Probing techniques including species composition sampling and high speed framing schlieren were employed to determine the penetration and mixing performance at several downstream locations. Our investigation consisted essentially of two parts. The first part was an investigation of the continuous jet. The performance of the continuous jet was mainly controlled by effective velocity ratio (r) as the square root of the momentum-flux ratio and the orifice diameter (d). The centerline trajectories of the jets and the maximum concentration decay were collapsed by the rd scale and the ratio of oncoming boundary-layer thickness to the injector diameter. The second part was an comparison of the performance between the pulse and continuous jets. The penetration of the pulse jet was adjustable by changing the pulse duty cycle at a condition of fixed injectant mass flow rate. Even at a condition of fixed injection pressure, the pulsed injection showed better mixing performance and the higher penetration, due to the fluctuation of the large-scale eddies in the jet associated with the fluctuation of the bow shock in front of the jet.

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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

    Space transportation system uses the liquid hydrogen of the fuel as a coolant of the engine. Therefore, it is necessary to predict the heat flux to the engine wall in high accuracy for efficient cooling with a minimum coolant. However, the prediction of the heat flux to the scramjet engine combustor walls, is quite difficult due to complex interaction of flow and combustion. In this study, a sidewall-compression-type scramjet engine was tested under Mach 6 flight conditions using Ramjet Engine Test Facility. The heat flux was measured using water-cooled heat-flux meters installed on the sidewall within the combustor sections. The experimental results were compared with CFD analysis of the whole engine to predict heat flux distribution on the engine wall. The numerical results of wall pressure distribution showed good agreement with the experimental data. However, the experimental results of heat flux were extremely higher than the numerical results due to the radiation heating which was not considered in the CFD analysis. Based on the results, the average heat flux of the sub-scale scramjet engine with 300 K isothermal walls was 1 MW/m2 in the stoichiometric fuel rate at Mach 6 flight conditions.

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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

    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 was addressed. © 2003 by the American Institute of Aeronautics and Astronautics, Inc. All rights reserved.

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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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  • 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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  • 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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  • 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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  • Numerical Experiments of Scramjet Combustion with Boundary-Layer Bleeding

    12th AIAA International Space Planes and Hypersonic Systems and Technologies  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

    日本機械学会流体工学部門講演会  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

    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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  • Effects of Reynolds Number on Scramjet Inlet Performance

    23rd International Symposium on Space Technology and Science  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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  • 推力向上のための混合促進手法の検証

    2007
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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

  • 先進流体計測が解き明かす後退翼における遷音速バフェットのメカニズム

    Grant number:18H03814  2018.04 - 2022.03

    日本学術振興会  科学研究費助成事業 基盤研究(A)  基盤研究(A)

    河内 俊憲, 小池 俊輔, 杉岡 洋介, 橋本 敦, 石田 崇

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

    2018年度に,風洞試験で用いる後退翼模型の製作,およびこれを用いた風洞試験による模型の安全性確認と基本的な空力特性の取得を行った.またこれら風洞試験に加えて,2断面同時可視化装置の開発を開始した.
    これら結果を踏まえ,本年度はまず研究のキーとなる計測システム,2断面同時断層シュリーレン可視化システムの確立を行った.2018年度の検討から,計測領域が広いと風洞設備と計測装置の干渉が不可避であることが分かった.他方で2018年度の実験から,計測領域を絞っても,衝撃波の横揺れを検出可能であることが分かった.これらを加味し,視野100 mm,奥行き(基準断面)±50 mm,被写界深度±10 mmを目標に,2断面同時可視化システムの設計・開発を行った.その結果,これら仕様を満たすシステムの確立に成功し,「風洞を用いない実験」においてその性能の確認が出来た.
    これら可視化システムの確立に加え,既存の1断面のみを可視化できる断層シュリーレン装置を風洞実験に適用し,後退翼の各スパン位置におけるバフェット特性の取得を行った.試験条件は2018年度の試験を元に,マッハ0.72,迎角7°,およびこれの比較対象迎角4°を選定した.これら試験では,計測システムを翼スパン方向にスイープさせ,翼スパンの3/4の領域において,後退翼における衝撃波振動のデータベースを世界で初めて作ることに成功した.
    またこれらの実験に加え,2020年度に行う非定常PSP計測や2断面同時断層シュリーレン計測を行うための治具の製作,また両計測の共存性をその設置方法や光源の干渉を含め検討を行い,両立可能であることを明らかにした.
    また風洞実験に対応する数値計算を行い,風洞壁が流れ場に及ぼす影響を明らかにし,翼根のみならず,翼端でも衝撃波の横揺れが生じる可能性があることを明らかにした.

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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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