Estimating heat-flux peak location and magnitude is important to efficiently design thermal protection systems of hypersonic vehicles, which are characterized by strict low-weight requirements. This work is a numerical study of hypersonic shock-wave/boundary-layer interaction experiments on flat plates and compression corners. In all the cases presented herein, shock-induced transition resulted in unusual heat-flux levels and distributions. Fully laminar and Reynolds-averaged Navier–Stokes simulations failed in predicting the heat-flux trends; however, by artificially triggering transition at specific location it was possible to enhance the agreement with the experiment and isolate the beginning of transition with reasonable precision.
All Science Journal Classification (ASJC) codes
- Aerospace Engineering