@inproceedings{oai:jaxa.repo.nii.ac.jp:00003478,
 author = {乾, 大知 and 高倉, 葉子 and Inui, Daichi and Takakura, Yoko},
 book = {宇宙航空研究開発機構特別資料: 第48回流体力学講演会/第34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 48th Fluid Dynamics Conference / the 34th Aerospace Numerical Simulation Symposium},
 month = {Dec},
 note = {第48回流体力学講演会/第34回航空宇宙数値シミュレーション技術シンポジウム (2016年7月6日-8日. 金沢歌劇座), 金沢市, 石川, 48th Fluid Dynamics Conference /the 34th Aerospace Numerical Simulation Symposium (July 6-8, 2016. The Kanazawa Theatre), Kanazawa, Ishikawa, Japan, The purpose of the present study about the supersonic parachute is to investigate the basic aerodynamic characteristics and the influences of perturbations by high-accuracy computation using the WENO scheme together with the HLLC flux Riemann solver. The simplified model with a rectangular concave shape is used without or with a sting model. The solutions for M∞=2.0 and M∞=3.0 are shown here. The Quasisteady flows are characterized by the detached bow shock wave from which vortices are shed and the shaking of the large subsonic region in the wake. The lift coefficients show fluctuations with low and high frequencies, and it has been indicated that the perturbations of inflow Mach number and the back pressure can cause oscillations of the detached bow shock waves. When the perturbation is impressed to the inflow Mach number, the location of the bow shock wave changes together with the pressure waves going and returning between the bow shock and the bottom of the concave body and the vortices shed from the center portion of the bow shock. When the sting is added to the concave body, the flow field suffers effects of the back pressure. Due to high back pressure, the thickness of boundary layer along the sting changes alternately in the upper and lower sides, with the position change of the bow shock., 形態: カラー図版あり, Physical characteristics: Original contains color illustrations, 資料番号: AA1630031003, レポート番号: JAXA-SP-16-007},
 pages = {51--56},
 publisher = {宇宙航空研究開発機構(JAXA), Japan Aerospace Exploration Agency (JAXA)},
 title = {凹状物体まわりの超音速流に関する振動特性},
 volume = {JAXA-SP-16-007},
 year = {2016}
}