@inproceedings{oai:jaxa.repo.nii.ac.jp:00038835,
 author = {石原, 知明 and 荻野, 要介 and 大西, 直文 and 澤田, 恵介 and 丹野, 英幸 and Ishihara, Tomoaki and Ogino, Yousuke and Ohnishi, Naofumi and Sawada, Keisuke and Tanno, Hideyuki},
 book = {54th AIAA Aerospace Sciences Meeting, AIAA SciTech},
 month = {Jan},
 note = {54th AIAA Aerospace Sciences Meeting (January 4-8, 2016. Hilton Orlando) San Diego, California, USA, The heat flux on the heat-shield and backshell of the Apollo capsule like test models with the roughness in the higher enthalpy conditions were computed using RANS and our developed high order code. Aeroheating measurements with the roughness induced transition on the heat-shield of an Apollo capsule model and on the backshell of a HTVR test model which was a manned space capsule were performed in the higher enthalpy conditions by the free-piston shock HIEST in JAXA. Measured data set indicate that heat flux on the heat-shield of the Apollo capsule model was 1.5-2 times larger than the heat flux in laminar How. On the other hand, the heat flux on the backshell of HTV-R became 2-4 times larger. In order to estimate accurate heat flux such turbulent How, a high order CFD code in hypersonic How was developed. On the heat-shield, RANS overestimated the measured data on the leeward surface especially in the high enthalpy conditions. This trend is not bad for the safe design of the TPS. On the other hand, RANS underestimates the peak heating of measured data on the backshell. The peak heat flux calculated by the high order code and fine mesh could obtain significant agreement with the measured peak heat flux., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AC1600105000, レポート番号: AIAA 2016-1127},
 publisher = {American Institute of Aeronautics and Astronautics(AIAA)},
 title = {Computation of Hypersonic Flow over a Reentry Capsule with Roughness Induced Transition},
 year = {2016}
}