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在高速飞行器再入大气的过程中,将出现严重的通讯中断问题。了解飞行器周围等离子体鞘套特性,是解决通讯中断问题的前提。为此,本文从简化Navier-Stokes方程出发,采用差分方法计算了小钝头锥体二组元扩散、化学平衡层流流场,给出了流场参数、电子密度、碰撞频率以及表面热流和阻力系数的分布。本文结果与边界层理论计算结果和无粘流场计算结果进行了比较。
During the reentry of the high-speed aircraft into the atmosphere, there will be a serious problem of communication interruption. Understanding the properties of the plasma sheath around the aircraft is a prerequisite for resolving the problem of communication disruption. Therefore, in this paper, based on the simplified Navier-Stokes equations, the differential method is used to calculate the two-component diffusion and chemical equilibrium laminar flow fields of small blunt nose cones. The flow field parameters, electron density, collision frequency and surface heat flux The distribution of drag coefficient. The results of this paper are compared with those calculated by boundary layer theory and non-viscous flow field.