Non-Equilibrium Flow in an Arcjet or a Shock Tube: Synthesis
The purpose of this test case is to obtain a better understanding of the non equilibrium flow field which exists in high enthalpy plasma tunnels. These tunnels are used to study the thermal protection system (TPS) for future spacecraft. To improve our understanding in the interpretation of measured data to enable proper extrapolation to flight it is mandatory to compute correctly these flow fields.
KeywordsShock Tube Thermal Protection System Cone Half Angle Inlet Cross Section Computational Validation
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