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1·The biggest lift drag ratio 3.36 considering viscous effects is obtained at Mach 6 when a proper base conical shock wave angle is chosen.

在设计点附近选取合适的半基准圆锥激波角并考虑粘性影响时，可得到乘波体最大升阻比为3.36；

2·The dynamic derivatives conception is used as the index for the vehicle stability, but it is looked as the function of angle of attack and Mach number to induced nonlinear characteristics.

采用自由振荡法数值模拟了平头、钝头外形的超声速俯仰振荡时间历程，并应用奇异分解线性最小二乘法辨识稳定性导数，得到动导数随马赫数和攻角非线性变化的规律。

3·The average effective pitch damping increases with increasing Angle of oscillation amplitude and decreases with increasing Mach number.

角振幅增大会使返回舱的平均俯仰阻尼增加，马赫数增大使俯仰阻尼降低。

4·Steady flow fields are also calculated to analyze flow field structure for the same cascade with different inlet Mach Numbers and incidence Angle.

对于同一叶栅进行了定常流场的计算与分析，比较了平面叶栅在不同进口马赫数、不同攻角下的定常流场。

5·And then the influence of the inlet flow's Mach, the outlet pressure, Angle, high velocity to the structure and major performance parameter of inlet's flow field are analyzed.

分析了来流马赫数、出口反压、攻角、高速旋转等因素对进气道流场结构及主要性能参数的影响。