Abstract
Abstract Investigations on the effects of high-temperature gas models have been performed by computing two-dimensional hypersonic flows. Thermal nonequilibrium effects are investigated by flow simulations around a vehicle of the Orbital Experiment along re-entry trajectory ranging from altitudes of 50 to 100 km, with the one-/two-temperature gas results being compared regarding the shock standoff distance, the heating rate and chemical species' concentrations. Additionally, calculations are performed for shock-tube flows in order to clarify the effects of the modelings included in the two-temperature model: the choice of chemical reaction constants, preferential dissociation and diffusive vibrational relaxation. Finally, a vibrational relaxation model for high-temperature gas without the need for information about immediately behind the shock wave is presented.
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