SIMULATIONS OF MESOFLAP FLOW CONTROL FOR RAMP OBLIQUE SHOCK/BOUNDARY LAYER INTERACTIONS

Abstract

A computational investigation was conducted of a novel flow-control method called mesoflaps for aeroelastic recirculation transpiration for ramp oblique shock/boundary layer interactions. In this flow control method, a series of flaps is placed over a cavity beneath the inception point of an oblique shock. The control of an SBLI for a 7.75 compression corner with mesoflaps revealed minor improvement of total pressure recovery as compared to a solid wall. However, the simulation of a 16 compression corner showed significant improvement in total pressure recovery for the flap cases as compared to the solid-wall case. The improvement increased as the deflections of the flaps increased when the deflections were less than or equal to the displacement thickness of the incoming boundary layer. Although the flap cases yielded increases in the displacement thickness and momentum thickness of the outgoing boundary layer as compared to the solid wall, the shape factor was maintained at approximately the same level.