EXPERIMENTAL STUDY OF EFFECT OF WEAK SHOCK WAVES ON SUPERSONIC BOUNDARY LAYER OF FLAT PLATE WITH BLUNT LEADING EDGE AT MACH NUMBER 2

Read more The experimental results of investigation of the effect of a pair of weak shock waves on the boundary layer of a flat plate with a blunt leading edge are presented at Mach number 2. Generation of weak shock waves was carried out using two-dimensional stickers 2.5 mm wide and 120 μm in thickness and 230 μm in thickness. The perturbations generated in the free flow have the configuration of N-wave. Its amplitude is 5 and 11 % respectively. In the boundary layer the generation of stationary longitudinal vortices by fronts of the N wave was detected. They do not spread downstream. The interaction of weak Mach waves with the boundary layer leads to an increase of the low-frequency vibrations of the shear layer.

Keywords:
supersonic flow, experimental investigations, flat plate with blunt leading edge, laminar-turbulent transition. 
УДК 532.526

EXPERIMENTAL STUDY OF EFFECT OF WEAK SHOCK WAVES ON SUPERSONIC BOUNDARY LAYER OF FLAT PLATE WITH BLUNT LEADING EDGE AT MACH NUMBER 2