@inproceedings{oai:jaxa.repo.nii.ac.jp:00003250,
 author = {松山, 新吾 and 藤田, 和央 and Matsuyama, Shingo and Fujita, Kazuhisa},
 book = {宇宙航空研究開発機構特別資料: 第49回流体力学講演会/第35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 49th Fluid Dynamics Conference / the 35th Aerospace Numerical Simulation Symposium},
 month = {Dec},
 note = {第49回流体力学講演会/第35回航空宇宙数値シミュレーション技術シンポジウム (2017年6月28日-30日. 国立オリンピック記念青少年総合センター), 渋谷区, 東京, 49th Fluid Dynamics Conference /the 35th Aerospace Numerical Simulation Symposium (June 28-30, 2017. National Olympics Memorial Youth Center), Shibuya-ku, Tokyo, Japan, This paper describes CFD application examples to predict hypersonic aerothermodynamics in design studies of a Mars entry capsule for future Japan’s Mars exploration mission. Firstly, two examples of the validation studies for the JAXA’s in-house CFD code against experimental measurements are briefly presented. CFD predictions of aeroheating are conducted for the T5 shock tunnel experiment at California Institute of Technology. The CFD results are generally in good agreement with the experimental data and show that the effects of wall catalysis played an important role. Hypersonic flow simulations are conducted for an experimental measurement of RCS jet interactions performed on the JAXA hypersonic wind tunnel facility. By comparing the simulated aerodynamic coefficients with experimental data for jet-on and jet-off cases, fair agreements between the CFD and the experiment are achieved. After the accuracy of simulation is validated, the flowfield data are examined further in detail to understand the interaction mechanism between RCS jets and hypersonic wake flows. The features of the wake flow with the RCS jet injection are very similar to those observed in an under-expanded jet in a supersonic crossflow. Finally, for a preliminary design study of Mars entry capsule, a CFD prediction of aerothermodynamic environment in hypersonic lifting flight is demonstrated along the planned nominal entry trajectory., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1730011016, レポート番号: JAXA-SP-17-004},
 pages = {110--115},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {火星突入カプセルの設計における CFD の適用事例 その1: 極超音速領域での熱空力解析},
 volume = {JAXA-SP-17-004},
 year = {2017}
}