Parameter Study for Scramjet Intake Concerning Wall Temperatures and Turbulence Modeling
Scramjets are hypersonic airbreathing engines that utilize the unique technology of supersonic combustion. Besides supersonic combustor and nozzle, the intake and subsequent isolator are the main components of a scramjet engine where the latter two are especially sensitive to the state of the boundary-layer. Shock wave boundary-layer interaction is of major concern in both compression components. Wall cooling and increased turbulence enhance the ability of boundary-layers to resist strong adverse pressure gradients and reduce separated flow areas, however, both are to some extent unknowns in the simulation of a shock-tunnel experiment. Thus a parameter study was initiated to investigate the influence of both factors on the current intake design for hypersonic testing at Mach 8.
KeywordsShock Wave Mach Number High Performance Computing Grid Block Reynolds Stress Model
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