NUMERICAL-SOLUTION OF 3-DIMENSIONAL SHOCK-WAVE AND TURBULENT BOUNDARY-LAYER INTERACTION

A newly developed, rapid numerical scheme is used to solve the complete mass-averaged Navier-Stokes equations for supersonic turbulent flow over a three-dimensional compression corner. A simple eddy viscosity model is developed, and the interaction of a swept shock wave and a three-dimensional turbulent boundary layer is studied. Good agreement is obtained between the present results and experimental measurements for the case of a wedge with angle α = 6 deg on a flat-plate sidewall. For the case of α = 12 deg, the computed results do not show the existence of a peak pressure found experimentally. However, the range of interaction, the plateau pressure, and the peak heat transfer are closely predicted for all cases. The high heat transfer near the axial corner is due to the thinning of the boundary layer and inflow of fresh high-momentum fluid. The heat transfer is relieved through pressure reduction and boundary-layer thickening. © 1978 American Institute of Aeronautics and Astronautics, Inc. All rights reserved.