The results of experimental study of the flow in the wing wake at Mach number range M = 2 - 4 and angle of attack of 10 degrees are presented. Experiments were carried out in supersonic wind tunnel T325 of ITAM SB RAS. Rectangular half-wing with sharp edges was used to generate vortex wake. Constant temperature hot-wire anemometer was used to measure mass flow and its pulsations. The hot-wire data were compared with 5-hole pressure probe data.
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