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Experimental investigations of supersonic turbulent flow over a compression ramp

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Experimental investigations of a 28 deg compression ramp which based on NPLS (Nano-tracer Planar Laser Scattering) and PIV technique are carried out in a Mach 3.0 low-noise wind tunnel, the incoming flow is supersonic turbulent flow (STF). Wave system can be observed by schlieren method, fine flow field structures is visualized via NPLS technique, density distribution is got by measurement based on image gray level analysis, velocity distribution is obtained using PIV technique which showed the separation region of flow field and revealed phenomenons of separation as well as reattachment.

Author(s):

WU Yu    
College of Aerospace Science and Engineering, National University of Defense Technology
China

YI ShiHe    
College of Aerospace Science and Engineering, National University of Defense Technology
China

CHEN Zhi    
College of Aerospace Science and Engineering, National University of Defense Technology
China