並列タイトル等An Approximate Analysis of Supersonic Turbulent Base Heat Transfer with Special Regard to The Effect of Boundary Layer Thickness
タイトル（掲載誌）航空宇宙技術研究所報告 = Technical Report of National Aerospace Laboratory TR-497
一般注記Base heat transfer of a two-dimensional bluff body in supersonic and hypersonic flows is analysed by the component analysis method, paying special attention to the effect of the approaching turbulent boundary layer thickness on the heat transfer rate. Turbulent mixing between the quiescent fluid in the wake and adjacent isentropic supersonic flow under constant pressure is assumed. Hill’s orgin shift method for the mixing layer is employed in order to deal with the finite thickness effect of the turbulent boundary layer. Heat transfer from the uniform flow to the base wall is analysed by taking account of two resistive elements:(1)heat transfer across the mixing layer, and (2)heat transfer between the recirculating flow and the base wall. The Prandtl number of the turbulent flow is assumed to be unity, and radiation is neglected. The base heat transfer rate is given in terms of the ratio of the boundary layer thickness to the base half-height, wall temperature ratio, and Mach number, stagnation pressure and stagnation temperature of an approaching uniform flow. Variations in the base heat transfer rate versus Mach number, wall temperature and boundary layer momentum thickness ratio are shown and compared with a certain available experimental data. The heat transfer rate shows the initial rapid increase and subsequent tendency to level-off with the increase in boundary layer thickness. Effects of boundary layer thickness on base pressure ratio and wake angle are also discussed.
資料番号: NALTR0497000
レポート番号: NAL TR-497
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=44750&item_no=1&attribute_id=31&file_no=1
連携機関・データベース国立情報学研究所 : 学術機関リポジトリデータベース（IRDB）（機関リポジトリ）
提供元機関・データベース宇宙航空研究開発機構 : 宇宙航空研究開発機構リポジトリ