采用数值手段研究了来流马赫数对飞机座舱附近区域气动加热的影响,计算的来流马赫数为0.8～2.0,基于翼展的雷诺教为107.通过分析飞机蒙皮表面的温度分布、表面摩擦因数、壁面法向速度梯度和热流量等物理量,给出了飞机头部座舱附近区域的气动热分布情况.计算结果表明,随着来流马赫数的增加,壁面法向速度梯度增大,飞机对称面上的平均温度、表面摩擦因数和热流量随之增大.此外,针对某型号飞机的计算结果表明,座舱附近区域上表面中心线上的平均温度与来流马赫数、自由来流温度之间呈一定的函数关系.%The effect of Mach number on aerodynamic heating is investigated numerically for the free-stream Mach number Ma∞ from 0. 8 to 2- 0 and Reynolds number 107 based on aircraft wingspan. The work provides an insight into the generation mechanism of aerodynamic heating based on some typical variables, including wall temperature, skin friction coefficient, velocity gradient in the normal direction and heat flux on the surface centerlines. Due to the growth of velocity gradient in the normal direction near the wall, the mean wall temperature, skin friction coefficient and heat flux on the surface center-lines increase with Ma∞. Moreover, there is a functional relation of the mean wall temperature along the centerline to free stream temperature and Ma∞.
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