@inproceedings{oai:jaxa.repo.nii.ac.jp:00014658,
 author = {中村, 弘明 and 真鍋, 圭司 and 瀬崎, 新士 and 西尾, 正富 and Nakamura, Hiroaki and Manabe, Keiji and Sezaki, Shinji and Nishio, Masatomi},
 book = {宇宙航行の力学シンポジウム　平成15年度, Symposium on Flight Mechanics and Astrodynamics 2003},
 month = {May},
 note = {Flow structures around a hypersonic re-entry Mars Environmental Survey (MESUR) capsule traveling at supersonic/hypersonic speeds are investigated utilizing a new computational method based on the finite element method (FEM). In order to confirm the validity of the computational method the results are compared with experimental ones obtained by the electrical discharge method for hypersonic flow at Mach 10. From these results, it can be concluded that they were in good agreement. As an example of the numerical simulation, flowfields around the capsule traveling at a speed of Mach 5, 3, and 2, respectively, are investigated. By these simulations, differences of the flow structures for various Mach numbers are clarified. The result shows that the location of the separation behind the capsule is governed by the strength of the reverse pressure gradient. The reverse flow behind the capsule that determines the value of the base pressure distribution is correlated to the strength of the re-circulation region and the stability of the capsule., 資料番号: AA0047120013},
 pages = {47--50},
 publisher = {宇宙航空研究開発機構宇宙科学研究本部, Institute of Space and Astronautical Science, Japan Aerospace Exploration Agency (JAXA/ISAS)},
 title = {超音速／極超音速で飛行する飛翔体周りの流れ構造の研究},
 year = {2004}
}