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运用结构化网格求解三维Euler方程,计算得到边界层外缘无粘流场气流参数;利用无粘流场气流参数和表面流函数的方法计算了飞行器无粘表面流线分布;在理论和半经验公式的基础上,计算了定比热比和变比热比情况下驻点热流密度,非驻点区域采用参考焓、局部相似性等方法来确定飞行器表面的气动加热,实现了数值算法与工程算法的耦合.上述方法用于求解高超声速钝双锥的表面热流分布,计算结果与经典的热流公式和实验结果进行对比,平均精度为10%左右,满足高超声速飞行器概念研究和初步设计的需要.
The three-dimensional Euler equation was solved by structured grid, and the flow parameters of the non-viscous flow around the outer boundary of the boundary layer were calculated. The streamline distribution of the non-stick surface of the aircraft was calculated by the flow parameters of the non-viscous flow field and the surface flow function. Based on the empirical formula, the stagnation heat flux density at fixed heat ratio and variable specific heat ratio is calculated, and the non-stagnation region adopts the method of reference enthalpy and local similarity to determine the aerodynamic heating of the aircraft surface. The numerical algorithm and The above method is used to solve the surface heat flow distribution of hypersonic blunt double cone. The calculated results are compared with the classical heat flow formula and the experimental results with an average precision of about 10%, which meets the concept and preliminary design of the hypersonic vehicle need.