並列タイトル等Measurements of Aerodynamic Damping Derivatives on Axial Symmetric Bodies in Hypersonic Flow
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-542
一般注記The aerodynamic damping derivatives on blunted cones and the AGARD HB-1, HB-2 models have been measured by use of an automatic free oscillation technique in the region of hypersonic flow. These data were obtained at a Mach number of 7.1, at Reynolds numbers from 0.3×10(exp 6) to 1.0×10(exp 6), and at reduced frequencies from 0.01 to 0.04. It is shown that the Embedded Newtonian theory agrees well with the experimental values including the effects of nose bluntness, angle of attack, and angle of flare on the unsteady aerodynamics of axial symmetric bodies. Also shown is that the aerodynamic damping derivative of a cone with a rotary axis Δx/l=0.292 takes the maximum value at dN/dB=0.06, when the nose bluntness is changed up to 0.3. On blunt-nose cylinder-flare bodies the effect of flare angle has been calculated by means of the approximation theory for a function of radial position in the inviscid shear flow profile.
資料番号: NALTR0542000
レポート番号: NAL TR-542
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