TRANSONIC SHOCK OSCILLATIONS ON NACA0012 AEROFOIL

The mechanism of the origin of shock oscillations on NACA0012 aerofoil s is investigated using a moving grid thin layer Navier Stokes code. T he method used to understand the mechanism is to initiate the shock os cillations on an aerofoil by moving the aerofoil from a regime of stea dy transonic flow into a regime of periodic flow by a change in airflo w incidence. The results indicate that the shock induced bubble plays a leading role in the origin of shock oscillations and the trailing ed ge has an affect on its amplitude.