Abstract
An investigation was conducted to evaluate the error involved in predicting aerothermodynamic loads (surface pressure, skin friction, and heat transfer) using a Reynolds Averaged Navier Stokes (RANS) solver. Numerical simulations of Shock Wave / Turbulent Boundary Layer Interaction (SWTBLI) at Mach 5 are performed and compared with vetted experimental data. These simulations include three 2-D impinging shock, and two 3-D swept shock cases. The impinging shock cases involve different levels of interaction intensity, which result in attached, incipiently separated, and fully separated flows. Comparisons between the numerical results and experimental data for each case are used to evaluate the error in predicting the associated SWTBLI aero-thermodynamic loads. The result shows that while wall pressure is accurately predicted, skin friction is under predicted, and heat transfer is over predicted. However, the trends in skin friction and heat transfer are captured by the RANS simulations.
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