一种高超声速飞行器全流道冷流流态的仿真研究及实验验证(英文)

The Full Flowpath Analysis of a Hypersonic Vehicle

对一种类X43-A吸气式高超飞行器全流道开展了M7一级的三维数值仿真研究,深入探索了进气道处于起动状态和不起动状态时全流道的冷流流场结构和和气动力特性,且部分结果与实验数据进行了对比。研究结果表明:(1)前体横截面上存在显著的展向压强梯度,使得经过预压缩的气流偏离了进气道进口,但同时也减少了进入内通道的边界层气流,提高了进口流场的品质;(2)后体喷流股的膨胀过程受到了周围外流的显著干扰,因而沿流动方向其截面形状不断发生变化,如在喷口附近为近似矩形,而在后体末端附近则演化为近似三角形;(3)当进气道处于不起动状态时,其全流道流动结构发生了显著变化,进气道的外部压缩波系往复振荡,尾喷管出口的喷流股也在不停的膨胀和收缩,具有极强的非定常特征;(4)当进气道处于不起动状态时,全机的气动力特性呈周期性变化,升阻比的变化幅度较大,在最大、最小值分别可达起动状态的2倍和1/4倍。另外,升力、阻力系数的变化曲线之间存在一定的相位差;(5)与实验结果的对照表明,所采用的数值仿真方法具有较高的精度。

A numerical study has been carried out to investigate the full flow path and aerodynamic characteristics of a hypersonic vehicle at a 7.0 free stream Mach number. Results indicate that the inlet started and unstarted operations have remarkable effects on the flow pattern of the full flow path. When the inlet operates in a started mode, the transverse pressure gradient generated by the forebody alters the air captured characteristics and the entering flow quality of the inlet. Furthermore, the expansion process of the nozzle jet flow is obviously affected by the external flow field around the afterbody with the cross section shape transiting from a near rectangle at the exit of the nozzle to a near triangle at the tail of the vehicle. When the inlet operates in an unstarted mode, the aerodynamic instability can be observed in the full flow path of the vehicle. Due to the oscillation of the external compressed shock wave and nozzle jet flow, the aerodynamic characteristics of the vehicle vary periodically with the lift-drag ratio changing from 0.25 to 2.09. Finally, by comparing to the experimental data, the reliability of the CFD is verified.