@inproceedings{oai:jaxa.repo.nii.ac.jp:00004134,
 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 Ohnish, Naofumi and Sawada, Keisuke and Tanno, Hideyuki},
 book = {宇宙航空研究開発機構特別資料, JAXA Special Publication},
 month = {Nov},
 note = {5th Symposium on Integrating CFD and Experiments in Aerodynamics (October 3-5, 2012, Chofu Aerospace Center, Japan Aerospace Exploration Agency (JAXA)), Chofu, Tokyo, Japan, Aeroheating measurements on the Apollo CM test model placed in the free-piston shock tunnel HIEST was conducted. Although the convective heat flux distributions along wall surface normalized by a product of Stanton number and the square root of the Reynolds number should fall on a single curve for laminar flow case, the measured data for high enthalpy conditions resulted in significantly larger than one for low enthalpy conditions. In the HIEST experiment, stagnation heat fluxes on small probes were also measured. We could find that the anomalous heating phenomena are not shown for small test model but for large one that is called the scaling effect of anomalous heating phenomena. Similar tendencies were also observed at other shock tunnels: NASA Ames 42-Inch Shock Tunnel, Caltec T5, and CUBRC LENS. The cause for those anomalous heating phenomena is yet unknown. Anomalous heating poses a critical issue over the existing design method of thermal protection system for entry capsules. To clarify the cause of it, we numerically investigate these two factors: The radiative heat transfer in the shock layer and the radiation heating from the driver gas. From the results of our computations, radiative heating from shock layer was negligibly small. While, obtained total heat flux considering radiative heating from driver gas agreed well with measured heat flux. Scaling effect of the anomalous heating phenomena was also explained by accounting for the radiation from the driver gas. Therefore, we can say that the radiative heating from the driver gas may be the cause of those phenomena., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA0062070026, レポート番号: JAXA-SP-13-001E},
 pages = {317--325},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {Numerical Study on Anomalous Heating over Apollo CM Test Model in Free-Piston Shock Tunnel HIEST},
 volume = {JAXA-SP-13-001E},
 year = {2013}
}