亚声速气动力采用面源法计算，高超声速气动力采用修正的牛顿流理论计算。

Panel Method was used for subsonic aerodynamic analysis, and the Modified Newtonian Impact Theory was used for hypersonic aerodynamic analysis.

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无论是采用牛顿·拉弗逊法还是其修正的方法，结果相差不多，特别是加载次数增多时，两者的计算数值趋于一致，所以其实质上是完全相同的。

The calculating results are almost equal whether Newton-Raphson method or its modified form is used, especially with more times of loading, which indicates that essential of the two methods is same.

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