攻角振荡对高超声速进气道性能影响数值模拟

Numerical simulation on effects of oscillatory angle of attack on performance of hypersonic inlet

应用重叠网格计算方法对高超声速飞行器出现攻角振荡时的发动机进气道的流场特性进行了数值模拟,给出了频率为10,20,40 Hz以及3°和5°振幅对进气道气动力、总压恢复系数和流量系数的影响,比较了飞行器在Ma∞=4,H=17 km爬升阶段和Ma∞=6,H=28 km巡航阶段攻角振荡对进气道性能参数的影响。计算结果表明,攻角的动态变化会造成进气道气动力、总压恢复系数和流量系数出现较大波动。

Since the oscillation of angle of attack will bring adverse effects on the performance of hypersonic inlet,computational fluid dynamics method and overlapping grid method are used to investigate the oscillations of the aerodynamic forces,pressure recovery coefficient and mass flow coefficient of a typical 2D inlet.The effects of frequency at 10,20,40 Hz and amplitude at 3°and 5°on inlet performance parameters are given in this paper,differences between climb phase with Ma∞=4 and H=17 km and cruise phase with Ma∞=6 and H=28 km of hypersonic aircraft are also presented.The results show that large oscillation occurs on aerodynamic force,pressure recovery coefficient and mass flow coefficient under the unsteady movement.These adverse effects will bring much challenge to the hypersonic craft and engine design if the oscillation of angle of attack could not be avoid.