並列タイトル等An Investigation of Support-Interference Effects 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-622
一般注記Support-interference effects on hypersonic base pressure are investigated for various geometrical sting-support configurations in the NAL Hypersonic Wind Tunnel. Base pressure and pressure distribution on the sting surface in the flow having a free-stream Mach number of 7.1 and a free-stream Reynolds number based on the unit length from 0.2×10(exp 5) to 2.0×10(exp 5)/cm were measured. The oil flow observation on the sting surface was made at the same time. The angle of attack of the model is 0deg. The models are four spherically blunted cones with a semi-vertex angle of 10deg, a nose bluntness radii of 0.3, 3, 8 and 15 mm and a base diameter of 100mm. The support system consists of a strut, sting-pod and a sting. Three different stings having different lengths of 530, 252.5, and 127.5mm are used to examine the sting-flare effect on the base pressure. Avoiding the strong base pressure rise caused by the effect of strut, the sting-flare corner effect is investigtaed. The experimental results show that the base pressure depends upon the Reynolds number and is affected by the interaction of the base recirculating flow and the separated flow around the sting-flare corner. This effect of the sting-flare corner becomes smaller as the length of the sting increases and the standard length of a sting which has a sufficiently minimal effect on the base pressure is obtained. Above a Reynolds number of about 1.0×10(exp 5)/cm, the base recirculating flow and the separated flow over the flare are independent of each other and the base pressure changes discontinuously at a Reynolds number of about 1.0×10(exp 5)/cm in many cases. It seems to be caused by the transition of the boundary layer on the model surface. In order to predict the base pressure of the sting-mounted models, the correlation of the base pressure with local flow properties, immediately preceeding the base, is discussed for those cases where there is little effect from the sting-flare and strut.
資料番号: NALTR0622000
レポート番号: NAL TR-622
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