Abstract
A study is conducted on supersonic flow at Mach number 1.65 over rectangular cavity of length-to-depth (L/D) ratio 3. Schlieren visualization revealed normal shock train like pattern in flow over the cavity. These shock structure are unsteady, and oscillated longitudinally inside the test section over the cavity. The oscillating shock train is eliminated, as the blockage produced by shear layer and boundary layer thickening due to pressure recovery in cavity is reduced by offsetting the cavity aft wall. The shock train—shear layer coupling is observed to completely suppress the third and higher modes of cavity oscillations.
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