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高超声速气动加热严重,考虑热化学非平衡对气动热环境影响,可以为热防护系统设计提供有效保障。采用Park和Gupta热化学非平衡模型,数值计算研究5组元(N_2,O_2,N,O,NO),17组化学反应的热化学非平衡效应对高超声速飞行器气动热环境影响,并与完全气体和热化学平衡模型进行对比分析。热化学非平衡模型流场温度及激波距离均比完全气体模型小。激波后气体密度因离解、化学反应而增大,且气体密度越大,激波距离越小,热化学平衡模型激波距离最小。完全气体和热化学平衡模型热流载荷计算值均比实验值偏大。Park和Gupta热化学非平衡模型数值计算激波距离及气动力载荷差别小。Park模型热流载荷计算值偏大,Gupta模型与实验结果相符,它可对气动热环境可靠预测。
Hypersonic aerodynamic heating serious, considering the thermochemical imbalance on the aerodynamic environment, can provide effective protection for thermal protection system design. Park and Gupta thermo-chemical unbalanced models were used to study the effects of 5 chemical elements (N 2, O 2, N, O, NO) and thermochemical non-equilibrium effects of 17 chemical reactions on aerodynamic thermal environment of hypersonic vehicles. Gas and thermochemical equilibrium model for comparative analysis. Thermo-chemical unbalanced model flow field temperature and shock distance are smaller than the complete gas model. The gas density increases due to dissociation and chemical reaction after the shock wave, and the larger the gas density, the smaller the distance of the shock wave, the smallest the shock wave distance of the thermochemical equilibrium model. The calculated values of the heat flow loads of the complete gas and thermochemical equilibrium models are all larger than the experimental values. Park and Gupta thermo-chemical non-equilibrium model numerical calculation of shock distance and aerodynamic load difference is small. The calculated value of the heat flow load in the Park model is large, and the Gupta model is in good agreement with the experimental results. It can predict the aerodynamic thermal environment reliably.