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Direct numerical simulation is performed on a 38.1% scale Hypersonic International Flight Research Experimentation Program Flight 5 forebody to study stationary crossflow instability. Computations use the US3D Navier–Stokes solver to simulate Mach 6 flow ...

Simulations of combustion in high-speed and supersonic flows need to account for autoignition phenomena, compressibility, and the effects of intense turbulence. In the present work, the evolution-variable manifold framework of Cymbalist and Dimotakis (“On ...

The relationship between freestream disturbances and measured pitot pressure spectra, defined as the transfer function, is investigated. Pitot probes used to characterize hypersonic facilities are considered for a variety of freestream conditions and flow-...

The modeling of the oxidation and sublimation of carbon-based ablative thermal protection system materials remains an area of active research. In this paper, two gas–surface interaction models for carbon are studied at representative reentry conditions. ...

An oxidation model for carbon surfaces has been developed where the gas–surface reaction mechanisms and corresponding rate parameters are based solely on observations from recent molecular beam experiments. In the experiments, a high-energy molecular beam ...