32th Congress of the International Council of the Aeronautical Sciences

03.3 - Basic Fluid Dynamics and Flow Control

STUDY ON THE HEAT FLUX OF HYPERSONIC SHOCK WAVE BOUNDARY LAYER INTERACTION CONTROLLED BY A MICRO-RAMP VORTEX GENERATOR

D. Sunč, C. Lič, H.-Y. Cai, School of Aeronautics, Northwestern Polytechnical University, China; Q.-L. Guoč, P.-X. Liuč, X.-X. Yuanč; čState Key Laboratory of Aerodynamics, China

Our study focuses on the application of micro-ramp vortex generator in hypersonic shock wave/boundary layer interaction. The elaborate structures of wake vortices are obtained. We reveal that the heating flux and friction will be significantly reduced due to the alteration of the flow patterns, which caused by vortical structures generated by the micro-ramp vortex generator.


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