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一个计算旋翼/机身/尾迹间非定常气动干扰的分析方法是建立在二阶升力线/全展自由涡模型和机身面元模型基础之上的。通过迭代机身在桨盘平面、尾迹定位点的诱导速度和旋翼/尾迹在机身表面的诱导速度，形成一个耦合的分析模型。在分析中计入了非定常项。作为算例，对两种孤立机身表面的平均压强系数分布以及旋翼机身组合体中机身表面的非定常压强系数分布进行了计算，其结果与实验值相吻合。
An analytical method to calculate unsteady aerodynamic disturbances between the rotor / fuselage / wake is based on the second-order lift line / all-span free-vortex model and the fuselage facet model. A coupled analytical model is formed by iterating the induction velocity of the fuselage on the plane of the propeller disk, the locating point of the wake and the induced velocity of the rotor / wake on the surface of the fuselage. Included in the analysis are unsteady items. As an example, the distribution of average pressure coefficient of two isolated fuselage surfaces and the distribution of unsteady pressure coefficient of the fuselage surface in the fuselage fuselage are calculated. The results are consistent with the experimental data.