National Aerospace Laboratory Aerodynamics Division
National Aerospace Laboratory Aerodynamics Division
National Aerospace Laboratory Aerodynamics Division
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
171 - 176
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
For blunt-nosed, ramped flat plates at angles of attack 0 deg, 20 deg, 30 deg, and 35 deg, heat transfer and flow field around compression ramp have been investigated experimentally based on infrared thermography measurement and schlieren photograph observation in the NAL 1.27 m hypersonic wind tunnel at M(sub infinity) = 10.0 and Re(sub infinity) = 1.5-2.3 x 10(exp 6)/m. Comparisons with CFD (Computational Fluid Dynamics) using NAL codes were also made for examination and comparison of the flow fields and the magnitude of heat transfer. The experimental results showed the increase of heat transfer on the flat plate upstream of corner and on the ramp when the leading-edge is blunt. However, for high angle of attack case, the reduction of peak heating on the ramp with increasing leading-edge bluntness which may caused by shock/shock interaction was observed. An analytical study to obtain a single correlation for the measured heat transfer along the plates showed that the ratio x/r(sub n) of x distance from leading-edge and nose radius, nose radius Reynolds number and viscous parameter based on local flow condition are dominant similarity parameters for heat transfer distribution on ramp down stream of reattachment as well as on flat plate part upstream of ramp corner except small bluntness case.
極超音速・圧縮ランプ回りの空力加熱特性
nalsp0037028.pdf
(891.65KB)
