Heating Augmentation for Short Hypersonic Protuberances

摘要

Computational aeroheating analyses of the Space Shuttle Orbiter plug-repair models are validated against datancollected in the Calspan—University of Buffalo Research Center 48 in. shock tunnel. The comparison shows that thenaverage difference between computed heat transfer results and the data is about 9.5%. Using computational fluidndynamics and wind-tunnel data, an empirical correlation for estimating heating augmentation on short hypersonicnprotuberances (k=u0001 < 0:3) is proposed. This proposed correlation is compared with several computed flightnsimulation cases and good agreement is achieved. Accordingly, this correlation is proposed for further investigationnon other short hypersonic protuberances for estimating heating augmentation.