Experimental study of compressible boundary layer on a cone at angles of attack

被引：0
|
作者：
A.Maslov [1 ]
D.Bountin [1 ]
A.Shiplyuk [1 ]
A.Sidorenko [1 ]
Q.Shen [2 ]
Z.Bi [2 ]
机构：
[1] Khristianovich Institute of Theoretical and Applied Mechanics(ITAM)and Novosibirsk State University
[2] China Academy of Aerospace Aerodynamics(CAAA)
来源：
Acta Mechanica Sinica | 2009年 / 25卷 / 03期
基金：
俄罗斯基础研究基金会;
关键词：
Compressible boundary layer; Transition; Experimental study;
D O I：
暂无
中图分类号：
O357.4 [边界层（附面层）理论];
学科分类号：
摘要：
Experimental study was conducted for boundary-layerson a sharp 5°half-angle cone of 400 mm length atangles of attack. The model was tested in the T-326 hypersonicwind tunnel (ITAM) at freestream Mach numberM = 5.95. Mean and fluctuation wall characteristics of theboundary layer are measured at 0°2°3°and 4°angles ofattack for different stagnation pressures. Pulsation measurementsare carried out by means of ALTP sensor. Pressureand temperature distributions along the model are obtained,and transition beginning and end locations have been found.Boundary layer stabilization with the increase of angle ofattack and the decrease of stagnation pressure is observed.High frequency pulsations inherent to hypersonic boundarylayer (second mode) have been detected.
引用
收藏
页码：325 / 333
页数：9
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