以某型中程弹道导弹头罩在工作时间内的气动加热为研究对象,采用数值求解N-S方程､k-ε湍流模型的方法,得到了导弹头罩温度、热流密度随速度变化的规律。结果表明:头罩在工作时间内随着导弹高度的上升和速度的增加头罩外部的温度增加,热流密度在速度为5Ma时最大,驻点位置在头罩尖端。

For researching aerodynamic heating of a certain type of medium-range ballistic missile's nose fairing in its working time, a turbulence model was used to solve Navier-Stokes equation. The aerodynamic heating conditions of ballistic missiles nose fairing during working time was calculated and analyzed. The rule that temperature, heat flux are changing with speed was obtained. Results shows that the temperature increases with the augment of the speed and altitude of missile, the max heat flux appears at the speed of Mach 5, stagnation point positions at the front end of nose fairing.