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针对复杂外形高超声速飞行器方案设计阶段的气动热计算效率问题,建立了高超声速飞行器气动热的快速工程计算方法。采用修正牛顿理论确定飞行器表面压力分布,利用牛顿最速下降理论计算飞行器表面流线分布,采用参考焓法、高温空气热力学特性的拟合公式以及热流密度的工程计算公式求出飞行器表面目标点的热流密度,计算了钝锥、升力体以及类乘波体的表面热流分布。仿真分析表明:该方法适用于复杂外形,且具有较高的计算效率和精度,能够满足复杂高超声速飞行器设计方案阶段气动热估算需求。
Aiming at the problem of aerodynamic heat calculation efficiency in the design stage of complex hypersonic vehicle, a fast engineering calculation method for aerodynamic heat of hypersonic vehicle is established. The modified Newton theory is used to determine the pressure distribution on the surface of the aircraft. Newton’s steepest descent theory is used to calculate the streamline distribution on the surface of the aircraft. The heat flux at the target point of the aircraft surface is obtained by the reference enthalpy method, the fitting formula of thermodynamic properties of high temperature air and the engineering calculation formula of heat flux Density, the distribution of the surface heat flux of the obtuse cone, the ascending body and the class of wave multipliers has been calculated. Simulation results show that the proposed method is suitable for complex shape, and has high computational efficiency and accuracy, which can meet aerodynamic thermal estimation requirements of complex hypersonic vehicle design stage.