Document Type: Article
Department of Aerospace Engineering, Sharif University, Tehran, Iran
Two Dimensional (2D) and Three Dimensional (3D) numerical simulations of an external compression supersonic ramped inlet for a free stream Mach number of 2 are presented. Comparison between numerical results and experimental data showed that multi-block structured gird using standard k-ε turbulence model gives acceptable results. The diffuser shape was then gradually varied to a circular one to encompass the Aerodynamic Interface Plane (AIP). It is observed that the 3D simulation predicted a more accurate static pressure distribution during the length of supersonic inlet and total pressure distribution at the AIP in comparison with the 2D one. Further, a better estimation of Shock Boundary Layer Interaction (SBLI), shock structure, and turbulent flow is predicted by the 3D simulation. It seems that, even though the 2D simulation scheme is widely used, it is a very weak method with low accuracy while the 3D simulation is more accurate and gives detailed flow field. Therefore; for cases where a detailed flow study along with an accurate prediction of flow parameters as well as the shock structure are required, the 3D numerical simulation must be applied.