Numerical investigations on the feasibility of the opposing jet through the extended nozzle applied to a forward heat shield of reentry capsule are reported. In the present CFD analyses, free stream condition was Mach 6.6. The test results show that this new device reduces both aerodynamic heating and aerodynamic drag on forward heat shield up to 90% and 91%, respectively. These results strongly suggest that this new device is one of the promising thermal protection systems for future supersonic and hypersonic flight vehicles.
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