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.