NUMERICAL SIMULATION OF SHOCK IMPINGEMENT ON BLUNT COWL LIP IN VISCOUS HYPERSONIC FLOWS

Abstract

The effect of shock impingement on the blunt leading edge of the cowl of a scramjet engine is investigated numerically. The flow-field is calculated by solving the full Navier-Stokes equations using the finite-volume, flux-splitting technique of van Leer, To resolve the finer details of the flow structure as well as to predict the surface heat transfer accurately, an adaptive-grid technique is used. The downstream effects are calculated by solving the thin-layer Navier-Stokes equations suitably modified for marching in space and iterating locally in time to steady-state solution at each spatial station. Results are compared with the available experimental and numerical results.