| 1 | Experimental study of compressible boundary layer on a cone at angles of attack显示文摘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. | A.Maslov D.Bountin A.Shiplyuk A.Sidorenko Q.Shen Z.Bi | 2009 | Acta Mechanica Sinica2009，25，3： | 2 |
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