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Asymptotic Solutions of the Thin Viscous Shock Layer Equations near the Symmetry Plane of Blunt Bodies in Hypersonic Rarefied Gas Flow

机译：高超声速稀薄气流中钝体对称面附近的薄粘性激波层方程的渐近解

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The hypersonic rarefied gas flow over blunt bodies near the symmetry plane is investigated for the regime transitional from continuum to free-molecular. Three rarefied gas flow regimes are considered depending on the relationship between the determining parameters of the problem. For all regimes, at small Reynolds numbers, asymptotic solutions of the thin viscous shock layer equations near the symmetry plane of blunt bodies are obtained in the form of simple analytical expressions for the heat transfer, skin friction and pressure coefficients as functions of the gas-dynamic parameters of the free-stream flow and the geometric parameters and temperature of the body. With decrease in the Reynolds number these coefficients approach their values in free-molecular flow (with the accommodation coefficient equal to unity). From comparison with the data calculated using the direct simulation Monte Carlo method, the accuracy and applicability limits of the analytical solution are estimated.
机译：研究了高超声速稀薄气体在对称平面附近钝体上的流动，研究了从连续体到自由分子过渡的过程。根据问题的确定参数之间的关系，考虑了三种稀疏气体流态。对于所有状态，在雷诺数较小的情况下，都可以通过简单的解析表达式来获得钝体对称面附近的薄粘性激波层方程的渐近解，这些表达式的传热，蒙皮摩擦和压力系数是气体的函数，自由流的动态参数以及人体的几何参数和温度。随着雷诺数的减少，这些系数在自由分子流中接近其值（调节系数等于1）。通过与使用直接模拟蒙特卡洛方法计算的数据进行比较，可以估算分析溶液的准确性和适用范围。

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