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Abstract: Flying condition with angle of attack is inevitable in a hypersonic vehicle, and it may influence the thermal protection system (TPS) performance of opposing jet and its combinations. A 3D Navier–Stokes equation and shear stress transfer (SST) k-ω model with compressible correction are employed to simulate the angle of attack characteristics of a blunt body with opposing jet and platelet transpiration TPS. The flowfield and heat flux transfer for angles of attack 0°, 3°, 6° with jet pressure ratio PR=0.1 and 0°, 6°, 12° with PR=0.2 are obtained. Numerical results show that the flowfield is no longer symmetrical with the effect of the angle of attack. The flowfield and heat transfer in windward and leeward performed adversely. The recompression shock wave in windward is strengthened, which increases local temperature and strengthens heat transfer. The opposing jet fails in thermal protection when the angle of attack reaches critical value; however, the critical angle of attack can be promoted by increasing PR. Finally, the transpiration gas can strengthen the cooling efficiency of windward, thereby, increasing the critical angle of attack.

高超声速飞行器逆向射流与层板发汗组合热防护的攻角特性分析

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