Visualization of Transonic Flows around an Airfoil with the Trip Strip in a Shock Tube

Abstract

Transonic flows around an airfoil with the trip strip in a shock tube were visualized to study applicability of the fixed transition technique to the shock tube airfoil experiment by the Schlieren method. The test Mach number and Reynolds number were 0.84 and 0.39 million, respectively. Schlieren photograghs showed that the fixed transition was realized at the transonic flow condition of the shock tube flows by the trip strip of small strips of plastics tape, distributed along the span of the model. Weak, but distingushable compression waves were also observed at the trip strip of some distribution pattern. The disturbance produced by the strips on the airfoil surface is three dinentional. So, further experimental work should be performed to evaluate the influence of such a disturbance on the present results by other quantitative methods.