Experimental study of compressible boundary layer on a cone at angles of attack |
| |
Authors: | A Maslov D Bountin A Shiplyuk A Sidorenko Q Shen Z Bi |
| |
Institution: | (1) Khristianovich Institute of Theoretical and Applied Mechanics (ITAM) and Novosibirsk State University, 630090 Novosibirsk, Russia;(2) China Academy of Aerospace Aerodynamics (CAAA), 100074 Beijing, China |
| |
Abstract: | Experimental study was conducted for boundary-layers on a sharp 5° half-angle cone of 400 mm length at angles of attack. The
model was tested in the T-326 hypersonic wind tunnel (ITAM) at freestream Mach number M = 5.95. Mean and fluctuation wall characteristics of the boundary layer are measured at 0°, 2°, 3° and 4° angles of attack
for different stagnation pressures. Pulsation measurements are carried out by means of ALTP sensor. Pressure and temperature
distributions along the model are obtained, and transition beginning and end locations have been found. Boundary layer stabilization
with the increase of angle of attack and the decrease of stagnation pressure is observed. High frequency pulsations inherent
to hypersonic boundary layer (second mode) have been detected. |
| |
Keywords: | Compressible boundary layer Transition Experimental study |
本文献已被 CNKI 维普 SpringerLink 等数据库收录! |