有翼再入飞行器的超/高超声速气动力工程方法

Aerodynamic Engineering Prediction Methods for Winged Reentry Vehicles

有翼再入飞行器气动力的工程计算方法尚有待进一步完善,计算精度有待进一步提高。文章根据有翼再入飞行器的气动布局特点,改进和发展了一套适于其气动布局的部件划分策略和压强计算选取准则。以此对航天飞机轨道器和类X-34飞行器的纵向气动力特性进行工程计算,并与其风洞试验和数值模拟结果进行对比分析。结果表明,文中的工程计算方法在马赫数3以上的超/高超声速范围内可准确预测有翼再入飞行器的升阻特性,其中升力系数和阻力系数误差小于10%;并可准确预测俯仰力矩特性随迎角改变的变化规律。与现有方法相比,文中的部件划分策略和压强计算选取准则在升阻特性精度相当情况下,可明显提高俯仰力矩的预测精度,并反映飞行器表面的压强分布特征。

Focused on the calculation inaccuracy of existing engineering prediction methods for winged reentry vehicles,a modified component partition strategy and pressure method selection rationale were developed.Through comparison of the experimental data and the engineering prediction on longitude aerodynamic characteristics of space shuttle orbiter and a X-34 like vehicle,it is shown that the prediction method can meet the accuracy requirements at Mach 3.0 or higher.The maximum relatively error is less than 10％ for lift coefficients and drag coefficients.Compared with the existing methods,the proposed strategy and rationale improves the prediction accuracy in pitching moment coefficient,with the same accuracy in lift and drag characteristics.Besides,the predictive pressure distribution is in agreement with the numerical results.