二维高超声速吸气式飞行器部件构型设计初步研究

Configuration design study for 2-D hypersonic airbreathing vehicle

对马赫数为6条件下不同部件构型的二维高超声速吸气式飞行器进行了数值模拟,分别比较了机身上表面采用卡门曲线和直线构型,燃烧室采用多级后向台阶和多级扩张直线构型,尾喷管采用幂曲线和直线构型对气动性能的影响.采用二阶精度的Roe格式和minmod限制器进行空间离散求解,使用Menter提出的k-ωSST(Shear stress transport)湍流模型模拟湍流流动,通过对壁面压力和摩擦力积分得到了各部件的升力、阻力和俯仰力矩,分析了每种部件构型对总体气动性能的影响,为高超声速吸气式飞行器构型设计提供了一定的依据.

A numerical study of different 2-D hypersonic airbreathing vehicle configurations under Mach 6 has been performed to analyze the aerodynamic characteristics, the airframe upper surface geometries considered in the present work include the Von Karman curve and straight line, the combustor configurations included the tandem backward facing step and tandem expansion straight line, the nozzle shapes included the power law curve and straight line. A second-order Roe scheme with a minmod limiter was used for space descretization, and Menter＇s k-ω SST（Shear stress transport） turbulence model was used for predic ting the turbulence flows, the CFD-derived pressure and friction distributions were numerically integrated to compute the lift, drag and pitch moment, and the influence of each configuration design on the global aerodynamic characteristics have been analyzed, which provided assistance for the design of the hypersonic airbreathing vehicle.