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The combustion gas tunnel is one of the main equipment used in the ground-test of the thermal protection system of supersonic aircraft. The assessment of the thermal protection system requires high uniformity of the flow field in the test system. The degree of matching between the pressure in the test cabin and the outlet pressure of the nozzle is a key factor affecting the uniformity of the flow field. The combustion reaction equations and CFD-FASTRAN are used to simulate the thermal environment of the gas tunnel. The gas component derived from the combustion reaction can provide a mixed gas model for numerical simulation. The shock wave characteristics of gas jet on the surface of a hemispherical-nose and cone body model are analyzed. The effects of different cabin pressures on the thermal environment of the model were analyzed. A new method for matching cabin and jet pressures is proposed.
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