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通过数值方法和基于无粘表面流线的工程快速方法,计算了空天飞行器基本型在Ma=8.0及Ma=10.2状态下的气动热特性。数值方法计算格式选用Roe的FDS格式,工程快速方法中飞行器的表面流线是通过基于直角网格的无粘Euler方程计算得到的,采用参考焓理论沿流线积分即得到沿流线的表面热流分布。结果表明,本文建立的气动热工程方法及数值方法得到的机身及机翼的热流分布与试验数据吻合较好,得到的驻点热流值与试验数据的误差小于5%。
The aerodynamic characteristics of the spacecraft with Ma = 8.0 and Ma = 10.2 are calculated by numerical method and engineering fast method based on non-stick surface streamline. The Roe FDS format is used to calculate the numerical method. The surface flow line of the aircraft in the rapid engineering method is calculated by the non-viscous Euler equation based on a rectangular grid. The reference surface enthalpy theory is used to obtain the surface heat flux distributed. The results show that the heat flow distributions of the fuselage and the wing obtained by the aerodynamic engineering and numerical methods established in this paper are in good agreement with the experimental data. The error between the stagnant heat flux and the experimental data is less than 5%.