@inproceedings{oai:jaxa.repo.nii.ac.jp:00003836,
 author = {棟石, 篤 and 宇賀神, 裕樹 and Muneishi, Atsushi and Ugajin, Hiroki},
 book = {宇宙航空研究開発機構特別資料: 第46回流体力学講演会/第32回航空宇宙数値シミュレーション技術シンポジウム論文集, JAXA Special Publication: Proceedings of the 46th Fluid Dynamics Conference / 32nd Aerospace Numerical Simulation Symposium},
 month = {Mar},
 note = {第46回流体力学講演会/第32回航空宇宙数値シミュレーション技術シンポジウム (2014年7月3日-4日. 弘前文化センター), 弘前市, 青森県, 46th Fluid Dynamics Conference / 32nd Aerospace Numerical Simulation Symposium (July 3-4, 2014. Hirosaki Bunka Center), Hirosaki, Aomori, Japan, The γ-Reθ Transition Model was applied to predict the supersonic boundary-layer transition on cones and the results were compared with flight experiments and wind tunnel ones. The model failed to predict important effects in high Mach number flows, i.e. higher mode instability, heat transfer and entropy layer. Although the prediction accuracy of the current γ-ReθTransition Model in high Mach number flows is not good, the distinctive advantages of the model such as low computation load and suitability for parallel computing are desirable and should be maintained in improvement to come. Fundamental data to make the correlation which involves the effects of Mach number, heat-transfer, entropy layer and cross-flow etc. are needed., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1530023001, レポート番号: JAXA-SP-14-010},
 pages = {1--6},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {超音速流れ中の円錐上境界層におけるγ-Reθ遷移モデルの検証},
 volume = {JAXA-SP-14-010},
 year = {2015}
}