COMPUTATION OF CROSSING SHOCK TURBULENT BOUNDARY-LAYER INTERACTION ATMACH-8.3

A three-dimensional hypersonic crossing shock wave/turbulent boundary- layer interaction is examined numerically at Mach 8.3. The test geomet ry consists of a pair of opposing sharp fins of angle alpha = 15 deg m ounted on a flat plate. Two theoretical models are evaluated. The full three-dimensional Reynolds-averaged Navier-Stokes equations are solve d using the Baldwin-Lomax and the Rodi (modified k-epsilon) turbulence models. Computed results for both cases show good agreement with expe riment for flat plate surface pressure and for flowfield profiles of p itot pressure and yaw angle, indicating that the flowfield is primaril y rotational and inviscid. Fair to poor agreement is obtained for surf ace heat transfer, indicating a need for more accurate turbulence mode ls. The overall flowfield structure is similar to that observed in pre vious crossing shock interaction studies.