並列タイトル等Calculation of Damping Derivatives for Arbitrary 3-Dimensional Bodies Using Newtonian Impact Theory
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-722
一般注記In order to calculate the aerodynamic characteristics of arbitrary 3-D bodies at very high Mach numbers, the Newtonian impact theory can be used by automatically determining the boundaries between exposed and shielded portions of the bodies. In the impact theory, the boundaries at a finite angle of attack are expressed as the relation of geometrical functions of body and a main flow direction. The functions of the boundary are more complicated on an ordinary winged body. For the sake of simplicity in the present analysis, it is assumed by Newtonian theory that the presure coefficients in the shielded portions are zero. The boundaries are easily determined by applying the proposed criteria to each panel of body surface. The pressure coefficients of the shielded portions of the body surface are excluded for the summation of the aerodynamic force. The predicted aerodynamic characteristics of a cone, a cone-cylinder, the Gemini type vehicle and the space shuttle are compared with those measured results.
資料番号: NALTR0722000
レポート番号: NAL TR-722
一次資料へのリンクURLhttps://jaxa.repo.nii.ac.jp/?action=repository_action_common_download&item_id=44979&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