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采用全Navier-Stokes方程的计算流体力学模拟技术研究了类HTV-2高超声速飞行器体襟翼局部分离流动特性,分析了不同飞行高度、壁面温度、飞行迎角等对流动分离特性的影响。研究表明:随着高度增加,壁面附近压力分布发生改变,沿着流向所形成的逆压梯度不断减小,使得体襟翼与飞行器表面附近的分离区减小;壁面温度增加导致压缩拐角(体襟翼与飞行器表面间)上游的流向速度梯度减小,即壁面粘性力减小,从而使分离区增大;随着迎角增加,压缩拐角内的逆压梯度增大,但上游流向速度梯度增加带来的黏性力增大更为明显,使流动更不容易发生分离,即分离区减小。
The whole separation flow characteristics of flaps of HTV-2 hypersonic vehicle are studied by computational fluid dynamics simulation based on the whole Navier-Stokes equation. The influence of different flight altitude, wall temperature and flight angle of attack on flow separation characteristics is analyzed. The results show that the distribution of pressure near the wall changes with the increase of the height, and the pressure gradient along the flow decreases continuously, so that the separation zone between the body flap and the aircraft surface decreases. The wall temperature increases, As the angle of attack increases, the pressure gradient in the compression corner increases, but the velocity gradient of upstream flow direction decreases with the increase of the angle of attack, Increasing the viscous force increases more obvious, so that the flow is more difficult to separate, that is, the separation zone decreases.