火箭飞行跨声速激波现象研究

The Study of Transonic Shock Wave during Launch Vehicle Flight

在运载火箭飞行过程中,由于火箭气动外形的变化,在跨声速飞行段运载火箭整流罩柱段外部会产生跨声速激波现象。为了研究火箭整流罩外部流场中跨声速激波的变化规律,采用三维数值模拟,获取了运载火箭跨声速飞行外部流场,并采用试验结果验证了数值方法的正确性。使用数值纹影对跨声速激波进行了显示,获取了激波位置随着飞行马赫数的变化规律,研究了激波前后压差随着飞行马赫数的变化规律。

Because of the variation of the launch vehicle profile,a transonic shock wave exists on the cylinder part of the fairing during the transonic flight.For the studying of variation of the transonic shock wave in the flow field around the rocket fairing,the flow field is obtained using a three-dimensional simulation and the method is validated by test data.The transonic shock wave is visualized by the numerical schlieren method,and the variation of the shock wave position with the Mach number of the far field flow is analyzed.The pressure difference across the shock wave characteristic with the far field Mach number is studied.