@inproceedings{oai:jaxa.repo.nii.ac.jp:00036752,
 author = {花光, 明 and 岸本, 啄司 and 尾藤, 日出夫 and Hanamitsu, Akira and Kishimoto, Takuji and Bito, Hideo},
 book = {航空宇宙技術研究所特別資料, Special Publication of National Aerospace Laboratory},
 month = {Jan},
 note = {航空宇宙技術研究所 8 Jun. 1995 東京 日本, National Aerospace Laboratory 8 Jun. 1995 Tokyo Japan, 衝撃波干渉加熱に対する実在ガスの影響を調べるために、HEG(ゲッチンゲン高エンタルピー衝撃風洞)で高エンタルピー衝撃風洞試験を行った。球体モデルと単純翼胴モデルの前縁沿いに熱移動分布が計測された。その右翼側後退角は55度、左側は60度である。流れの可視化もまたLIF(レーザ誘導蛍光)方式で単純翼胴モデルを使い行われた。計算流体力学(CFD)解析は、球体モデルに沿って冷凍流れと平衡空気流れの両方の条件でその熱移動分布について行われた。実験での良い配置は、平衡空気流れの条件で得られた。, High enthalpy shock tunnel test was performed at HEG (High Enthalpy Shock Tunnel in Goettingen) to examine the real gas effect on shock interference heating. Heat transfer distributions were measured along the sphere model and the leading edge of simple wing-body model, whose sweep-back angle on the starboard side is 55 deg and on the port side is 60 deg. Flow visualization was also made for simple wing-body model by LIF (Laser Induced Fluorescence) method. CFD (Computational Fluid Dynamics) analysis has been performed about the heat transfer distribution along the sphere model both in the conditions of frozen flow and equilibrium air flow. Good agreement with experiment was achieved in the condition of equilibrium air flow., 資料番号: AA0000110002, レポート番号: NAL SP-29},
 pages = {10--16},
 publisher = {航空宇宙技術研究所, National Aerospace Laboratory (NAL)},
 title = {High enthalpy flow computation and experiment around the simple bodies},
 volume = {29},
 year = {1996}
}