Abstract
Reynolds-Averaged Navier Stokes computational fluid dynamics was used to simulate shock-boundary layer interactions on a zero-incidence cylinder incurred by an impinging planar shock wave in a supersonic Mach 3 flow. The simulations emulated the 1983 Brosh and Kussoy experimental test case conducted at NASA Ames Research Center. The simulations revealed complex and highly three-dimensional aerodynamic flow structures, such as recirculation/separation bubbles, multiple reflected shocks and expansion fans, crossflow interaction from windward to leeward sides of the cylinder and wake type flow on the leeward cylinder side. The axial and radial pressure profiles through the windward and leeward boundary layers, coupled with detailed flow visualization, revealed significant insight into the physics of the interactions. Numerical studies included varying turbulence freestream parameters, turbulence models and grid density. The various numerical models, except for one, generally compared reasonably well to experiment. The largest discrepancies occurred in regions of very low speed/separated/wake-type flow.
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