並列タイトル等Wind Tunnel Experiments on Non-Axisymmetric Blunt Bodies with Flat Faces in Supersonic Flow
タイトル（掲載誌）航空宇宙技術研究所資料 = Technical Memorandum of National Aerospace Laboratory
一般注記The flow field around a non-axisymmetric blunt body with a flat face in supersonic flow is important in relation to the aerodynamic problems of a reentry vehicle like a shuttle orbiter at large angles of attack.Much attention has been paid to axisymmetric bodies experimentally as well as theoretically,and results are available.By contrast,the flow field about a delta-faced body,which is a basic form of lifting bodies like the shuttle orbiter,is not clarified.Five models including circular-faced,elliptic-faced,clover-faced,and delta-faced cylindrical bodies,are taken up for the purpose of pressure measurements and oil flow tests on the windward flat faces.These models can be divided into two groups: one is the group whose members have smooth and continuous shoulder lines,the other the delta-faced body which has three sharp corners on the side.There are three important points in the present experimets.1.The first is to obtain the pressure distributions on the flat-faced bodies with various shoulder lines and to compare them.2.The second is to obtain evidence of supersonic as well as subsonic regions near the shoulders.3.The third is to examine the behavior of the stagnation point on the flat face against angles of attack.This paper presents the experimental results for the problems stated above.The experiments were performed at Mach numbers from 1.5 to 3.0,at angles of attack from -15°to 15°,and a Reynolds number of about (2.5～4)×107/m in NAL’s 1m×1m supersonic wind tunnel.First we conducted pressure measurements on the circular-faced body.The flow on the circular-face expands gradually from the stagnation point to the shoulder and it becomes sonic at the shoulder itself;the sonic lines on the face occur along the shoulder only.Present measurements show that all bodies including the delta-faced body have these features and supersonic regions do not exist except at their shoulders at small angles of attack.The pressure distribution according to the expansion of the flow from a stagnation point to the shouies of the first group like the clover-face body is quite similar to that of the circular-face one.However the pressure distributions for the delta-face body are fairly different with the increase of the Mach number.Particularly,a wide stagnation region seems to appear at M∞=2.5 and α=-5°.Further increase in the Mach number results in this wide stagnation region growing into two stagnation points.
資料番号: NALTM0349000
レポート番号: NAL TM-349
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