Numerical Simulation Of Supersonic Compression Ramp Flow

Shock wave/boundary layer interaction (SWBLI) is a highly critical problem that occurs in aircraft transonic or supersonic flow. This study performed CFD analysis of the ramp flow freestream Mach number 2.79. To secure reliability analysis, adaptive mesh refinement using gradient p sensor was used. Through this, grid sufficient resolution obtained for region shock wave, expansion and separation. The prediction performance 7 turbulence models are widely used engineering application were compared. baseline k–ω two-equation model showed best performance, while SST model, which one most models, 2 Reynolds stress relatively poor performance. In SWBLI problem, use made it possible to resolution; meanwhile, comparison various confirmed generally somewhat inappropriate.