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为快速准确预测高超声速飞行器驻点热流密度,基于P-R状态方程,计算空气真实气体状态下比热比、定压比热容,得到温度拟合公式。应用变比热计算了高超声速飞行器激波后温度,应用空气真实气体状态下定压比热容计算了典型的高超声速钝头体驻点热流密度值。计算结果与实验值基本吻合,表明计算方法可行,有足够的精度,可为高超声速飞行器初步设计热环境计算和防热材料的合理选择提供可靠的参考数据。
In order to predict the stagnation heat flux of the hypersonic vehicle quickly and accurately, the specific heat capacity and specific heat capacity of the air are calculated based on the P-R equation of state, and the temperature fitting formula is obtained. The specific heat was used to calculate the post-shock temperature of the hypersonic vehicle, and the heat sink density of the typical high-velocity blunt body was calculated using the specific heat capacity under constant pressure in the air. The calculation results are in good agreement with the experimental ones, which shows that the calculation method is feasible and has enough accuracy, which can provide reliable reference data for the calculation of thermal environment and the reasonable choice of heat-proof materials for the initial design of hypersonic vehicles.