Abstract
An experimental attempt was made to suppress self-excited shock wave oscillation on a 2D symmetrical circular-arc airfoil in internal transonic flow by using a row of holes passing the airfoil. Flow was visualized by Schliren method, and shock wave positions were measured by line scan camera. The result shows that a row of holes passing the airfoil can suppress RMS of shock wave positions, boundary layer and wake flow to about 40 percent without large effects on mean positions and peak frequency of shock wave oscillation.
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