Abstract
Understanding of hypersonic viscous interaction phenomenon over control surfaces is of particular impor-tance for designers of hypersonic vehicles. An experimental study of the behaviour of hypersonic flow past flaps is presented in this report. Impulsive glow discharge technique and Schlieren visualization using high speed video camera are applied to examining the structure upstream of the hinge. These experiments are conducted in a hypersonic gun tunnel at Mach number 10 and at Reynolds numbers based on the chord length ranging 0.8 - 2.12 × 105. The flap deflection angles studied are in the range from 0 to 0.523 rad at zero incidence. Numerical simulations based on the Navier-Stokes equations are also performed. Time lines obtained by the dis-charge technique are reasonable and the structure evaluated by the time lines correlates well with those through Schlieren and computational results. Normalized upstream influence increases with increasing Reynolds number and increasing flap angle in the range studied.
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