Computational Analysis of Inlet Aerodynamics for a Hypersonic Research Vehicle

The aim of the present work is to carry out Reynolds-averaged Navier-Stokes computations of flow through the inlet of a hypersonic research vehicle with a view to accomplish detailed aerodynamic analysis. Three inlet configurations that differ in the inlet-duct height are considered in this study. The results of this study are13; presented in the form of detailed computational flow visualization through density contours, variation of flow parameters at various desired sections, and inlet performance in each case.