高马赫数下横/逆向喷流干扰流场数值研究

横向喷流和逆向喷流广泛用于高超声速飞行器气动力与气动热控制。采用格心型非结构有限体积法求解基于三温度热化学非平衡模型的全Navier-Stokes方程，对高空、高马赫数来流条件下二维圆柱状构型飞行器的喷流干扰流场进行数值模拟，研究了仅存在横向或逆向喷流以及横/逆向喷流同时存在时的复杂流场结构以及喷流降低热流、减阻、改善升力的具体效果。通过控制变量的方法，探究了不同参数（马赫数、静压）的喷流对流场结构及飞行器的气动力、气动热的影响规律。结果表明：在一定条件下，当逆向喷流与横向喷流同时存在时，下游的横向喷流可以影响到上游的逆向喷流流场结构；逆向喷流可以显著减小高超飞行器阻力，并降低头部壁面热流峰值，而横向喷流对高超飞行器的升力特性有一定提高；在横向喷流已用于飞行器姿态控制的情况下，一定条件下可以同时使用逆向喷流，既可以减阻、又可以降低热流峰值，还可以提升升力。

Numerical study on transverse/opposing jet interaction flowfield under high Mach number

Transverse and opposing jets are widely used in aerodynamic and aerothermal control on hypersonic vehicles. To solve Navier-Stokes equations, this paper, based on three-temperature thermochemical nonequilibrium model, numerically simulated jet interferences on a two-dimensional cylindrical vehicle at high altitude under high Mach number by employing the finite volume method in the cell-centered scheme. The flowfield structures with only transverse/opposing jet and both the two jets and the influence of jet interaction on heat flux reduction, drag reduction and lift improvement were studied. By variable control, the effects of jet flow with different parameters (Mach number, static pressure) on flow field structure and aerodynamic force/heat of aircraft were explored. The results show that in some cases, the flowfield structure of the upstream opposing jet interaction can be influenced by the downstream transverse jet when both the two jets exist in hypersonic freestream. The opposing jet can significantly lower the drag of the hypersonic vehicle and reduce the peak wall heat flux on the head of the vehicle. The lift characteristic of hypersonic vehicle can be improved by the transverse jet flow. In the case that the transverse jet has been used for aircraft attitude control, the opposing jet can be simultaneously used under certain conditions, which can not only reduce drag and peak heat flux, but also increase lift.