Kawasaki Heavy Industries Ltd Akashi Technical Institute
Kawasaki Heavy Industries Ltd Akashi Technical Institute
Kawasaki Heavy Industries Ltd Akashi Technical Institute
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: 第11回航空機計算空気力学シンポジウム論文集
雑誌名(英)
Special Publication of National Aerospace Laboratory: Proceedings of the 11th NAL Symposium on aircraft computational aerodynamics
巻
22
ページ
85 - 89
発行年
1994-03
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 10-11 Jun. 1993 東京 日本
会議概要（会議名, 開催地, 会期, 主催者等）（英）
National Aerospace Laboratory 10-11 Jun. 1993 Tokyo Japan
Toward the 21th century, some hypersonic wind tunnels for development of space planes and supersonic transports are under construction and planned in Japan. For designing these wind tunnels, it is indispensable to make use of CFD (Computational Fluid Dynamics) technology. This paper describes a numerical simulation of the nozzle flow of a hypersonic wind tunnel. The flow through the hypersonic axisymmetric nozzle with exit Mach number 7.0, which was installed in the hypersonic wind tunnel of National Aerospace Laboratory (NAL), was calculated by using three dimensional Navier-Stokes codes with q - omega model of turbulence by T.J. Coakley. The calculated results were compared with the experimental data, which had also been obtained by NAL, on the flow distributions at nozzle exit. Comparison with experiment and calculation shows a reasonable agreement. The effect of wall conditions such as adiabatic wall or isothermal wall upon the exit flow distributions was also investigated by numerical simulation.
極超音速風洞ノズルの流れの数値解析
nalsp0022014.pdf
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