Investigation of flowfield around hypersonic space plane

Autor:	Nakamura, Hiroaki, Manabe, Keiji, Sezaki, Shinji, Nishio, Masatomi
Jazyk:	japonština
Rok vydání:	2003
Předmět:	SSTO vehicle 流れ場 仰角 angle of attack 極超音速飛行 boundary layer 境界層 electric discharge model research and development 数値シミュレーション laminar flow 壁表面 numerical simulation 層流 hypersonic flight wall surface スペースプレーン space plane flow visualization SSTO機 放電モデル flow field 研究開発 流れの可視化
Zdroj:	宇宙航行の力学シンポジウム 平成14年度 = Symposium on Flight Mechanics and Astrodynamics 2002. :63-66
Popis:	The flowfield analysis around a model of space plane traveling at Mach 10 has been carried out utilizing the Electric Discharge Method and the Finite Element Method (FEM) scheme. The Electric Discharge Method can visualize almost all important hypersonic flowfield phenomena, such as three-dimensional shock shapes, streamlines near wall surface, distant streamlines from wall surface, boundary layers, etc. In this study, the experiments and the numerical simulations were carried out under the conditions the angles of attack were 0 and 10 deg. Furthermore, the experimental results were compared with the numerical ones. In these comparisons, it was found that they were relatively in good agreement. 資料番号: AA0045913017
Databáze:	OpenAIRE
Externí odkaz:	https://explore.openaire.eu/search/publication?articleId=jairo_______::9eb5fe750a16d2b40b8bd3364fd57848 http://id.nii.ac.jp/1696/00014698/ Zobrazit plný text záznamu