Mitsubishi Electric Corporation Kamakura Works
Mitsubishi Electric Corporation Kamakura Works
Mitsubishi Electric Corporation Kamakura Works
Mitsubishi Electric Corporation Kamakura Works
Kyushu University Department of Aeronautics and Astronautics, Faculty of Engineering
Kyushu University Department of Aeronautics and Astronautics, Faculty of Engineering
出版者
航空宇宙技術研究所
出版者（英）
National Aerospace Laboratory (NAL)
雑誌名
航空宇宙技術研究所特別資料
雑誌名(英)
Special Publication of National Aerospace Laboratory
巻
37
ページ
165 - 170
発行年
1998-02
会議概要（会議名, 開催地, 会期, 主催者等）
航空宇宙技術研究所 12-13 Jun. 1997 東京 日本
会議概要（会議名, 開催地, 会期, 主催者等）（英）
National Aerospace Laboratory 12-13 Jun. 1997 Tokyo Japan
In the present study, heat protection due to mass addition on the blunt body is experimentally and numerically investigated. Experiments are conducted by using a conventional blowdown-type wind tunnel. For the experiments on heat protection with mass addition, a hemisphere model is used and the coolant N2 gas is supplied tangentially through a slot. Significant decreases of surface heat flux are obtained. In numerical analysis, axisymmetric full Navier-Stokes equations are solved by an implicit finite difference method. LU-SGS (Lower-Upper-Symmetric Gauss-Seidel) and AUSMDV (Advection Upstream Splitting Method DV) scheme are applied. The k-epsilon turbulence model accounting for both compressibility and low Reynolds-number effects is also incorporated. The numerical results show good agreements with experiments. More detailed investigation of the flow inside the boundary layer indicates that the boundary layer is consists of two sub layers and that the inner layer plays a role like adiabatic wall structure on the surface. These characteristics are considered to be most essential in the determination of film cooling effects in this type of hypersonic flow.
フィルムクーリング冷却法による極超音速流中の物体のまわりの空力加熱の減少について
nalsp0037027.pdf
(789.78KB)
