Abstract
A full Navier-Stokes (FNS) computation was carried out on a mixed-compression axisymmetric scramjet inlet at Mach 5. The geometry including a blunt nose and cowl leading edge was modeled using a multizone approach which permitted running either time-marching or space-marching on individual zones. A Baldwin-Lomax turbulence model was used to simulate the effects of turbulence. The flow solution agreed very well with the test data on the wall static pressure and throat total pressure. The inlet performance calculated by postprocessing the solution matched the wind-tunnel test data as well.
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