Faculty Profiles - KOUCHI Toshinori

MISC - KOUCHI Toshinori

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高レイノルズ数空力を支える流体計測とデータ駆動型解析の試み Invited

河内俊憲

第488回航空懇談会 2023.9

航空機の設計・開発を支える先進流体計測とデータ駆動型解析 Invited

河内俊憲

2022年度日本冷凍空調学会年次大会 2022.9

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

貝原涼弥, 黒瀬章弘, 河内俊憲

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

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

菊池翼, 福本翔太, 田中健人, 竹内孔一, 河内俊憲

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

Supersonic wind tunnel introducing mainstream turbulence without a Laval nozzle

清水崇史, 福田光一, 田中健人, 鈴木博貴, 河内俊憲

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

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

貝原涼弥, 田中健人, 鈴木博貴, 河内俊憲

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

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

河内俊憲, 福本翔太, 杉岡洋介, 小池俊輔

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

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

渡邉大成, 田中健人, 鈴木博貴, 河内俊憲

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

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

福本翔太, 河内俊憲, 杉岡洋介, 小池俊輔

飛行機シンポジウム講演集(CD-ROM) 60th 2022

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

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

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

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

SANSICA Andrea, HASHIMOTO Atsushi, KOIKE Shunsuke, KOCHI Toshinori

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

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

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

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 ( 3 ) 82 - 92 2021

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

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

DOI： 10.2322/jjsass.70.82

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

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

細谷昌平, 永田靖典, 河内俊憲, 竹腰正雄, 高橋政浩, 富岡定毅

宇宙科学技術連合講演会講演集(CD-ROM) 65th 2021

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

大寺健吾, 河内俊憲, 福本翔太, 杉岡洋介, 小池俊輔

飛行機シンポジウム講演集(CD-ROM) 59th 2021

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

中川貴裕, 丸山裕也, 河内俊憲

宇宙科学技術連合講演会講演集(CD-ROM) 65th 2021

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

IWACHIDO Masaki, KOUCHI Toshinori, YANASE Shinichiro, NAKANISHI Yusuke

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

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

丸山裕也, 河内俊憲, 中川貴裕, 青木礼

宇宙科学技術連合講演会講演集(CD-ROM) 65th 2021

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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