Robert WATT, Rowan GOLLAN, Nicholas GIBBONS

DOI Number: 10.82241/ceas-hisst-2024-276

Conference number: HiSST-2024-276

The thermal non-equilibrium state of the gas at the exit of shock tunnel nozzles can have a signifi- cant effect on the flow over the test article. The most common modelling of thermal nonequilibrium for hypersonic nozzle flows represents the non-equilibrium state using two temperatures: one for the translation and rotation; and one for the average vibration of all the molecules. In this paper, we extend this model to account for a vibration temperature for each molecule, and compare to the more common approach of using two temperatures. Simulation of nozzle flows at high enthalpy conditions in the T4 shock tunnel facility will be used for the investigation.

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In Categories: 1.Events, HiSST 2024, Testing & Evaluation
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