並列タイトル等Aerodynamic Heating Analysis for Axisymmetric Bodies in Supersonic Flow
タイトル（掲載誌）航空宇宙技術研究所特別資料 = Special Publication of National Aerospace Laboratory SP-16
一般注記Aerodynamic heating analyses have been performed for axisymmetric bodies in the supersonic flow. both experiments using a shock tunnel and the computations corresponding to the experiments are conducted. Heat flux to the bodies such as a hemisphere-cylinder and an ogive-cylinder are measured. Flow conditions are (1) Mach number M infinity = 4.25 (2) Reynolds numbers Re infinity = 2 - 3x105, based on body radius (3) Stagnation temperatures T0 = 500 - 600K (4) Angle of attack alpha = 0 degrees Results of the experiments and the computations are summarized as follows. Heat flux to the hemisphere surface has the maximum value at the stagnation point and decreases smoothly downstream. Also the heat flux to the ogive surface is quite large in the vicinity of the tip and decreases gradually downstream in the case of fully laminar or fully turbulent flow. In the case of the flow including the transition, increase of heat flux caused by the transition of the boundary layer is observed. LU-ADI difference scheme for compressible Navier-Stokes Code has been used for the computations corresponding to the experiments. Computational results show good correlation to the experimental data obtained by the shock tunnel.
資料番号: NALSP0016039
レポート番号: NAL SP-16
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