Based on the Computational Fluid Dynamics (CFD) approach, an aerothermal calculation model verified by the wind tunnel test is established, and the influences of angle of attack, wall temperature, static temperature of the incoming flow, wall temperature ratio, Mach number and Reynolds number of incoming flow on the aerothermal characteristics of the forebody are analyzed in detail. The obtained results indicate that the relationship between the surface heat flux and the angle of attack is approximately linear, as well as the relationship between the heat flux and the wall temperature. However, the relationship between the heat flux and the static temperature of the incoming flow is nonlinear. The wall temperature ratio of zero point of heat flux in the same state is basically the same, and this is independent of the static temperature of the incoming heat flux. The function relationship between the near wall fluid temperature and the wall temperature is established, and the predicted results are in good agreement with the function curve. Based on the temperature function of the near wall fluid, the heat flux conversion formula of different static temperatures are established to form the heat flux estimation approach, and the estimated value is in good agreement with the predicted results. The heat flux distributions of the forebody with different Mach numbers are basically the same, and the heat flux increases approximately linearly with the increase of Mach number. The heat flux distribution law of the forebody with different Reynolds numbers is basically the same, and the heat flux increases with the increase of Reynolds number. Besides, the position of the maximum of the fluid temperature in the boundary layer is close to the wall with the increase of the Reynolds number.

基于计算流体动力学（CFD）方法，建立了经过风洞试验验证的气动热计算模型，研究了攻角、壁温、来流静温、壁温比、马赫数和雷诺数的影响对前体的空气热特性进行了详细分析。得到的结果表明，表面热通量与攻角之间的关系近似线性，热通量与壁温之间的关系也是如此。然而，热通量与流入流的静态温度之间的关系是非线性的。相同状态下热通量零点壁温比基本相同，这与传入热通量的静态温度无关。建立了近壁流体温度与壁温的函数关系，预测结果与函数曲线吻合较好。基于近壁流体的温度函数，建立了不同静态温度下的热通量换算公式，形成了热通量估计方法，估计值与预测结果吻合较好。不同马赫数前体的热通量分布基本相同，且随着马赫数的增加，热通量近似线性增加。不同雷诺数前体的热流分布规律基本相同，热通量随着雷诺数的增加而增加。此外，随着雷诺数的增加，边界层中流体温度最大值的位置靠近壁面。