Turbulent heat transfer during Mars Venus and Earth atmospheric entry

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This project aims to design better heat shields for spacecraft. Designing heat shields for re-entry vehicles needs good models to predict aerodynamic heating. Conventional wind tunnels cannot measure aerodynamic heating in ground tests in the region of peak heating, making design uncertain and risky. This project will use a free-piston-driven expansion tunnel that can produce flows fast and dense enough to measure heating for turbulent boundary layers at the highest speeds encountered during re-entry. This should allow scientists to test and develop theoretical and numerical models of heating and so improve spacecraft design.