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建立了旋翼升力线模型和广义尾迹模型，在计算角迹涡线诱导速度时，采用了快速收效方法。以AH－1G“眼镜蛇”直升机悬停旋翼在火箭轨道上的诱导速度分布为算例，数值结果与Landgrebe的预定尾迹旋翼入流模型分析结果作了对比，两者吻合较好。
The rotor lift line model and the generalized wake model are established. When calculating the induced velocity of the vortex trail, a fast approach is adopted. Taking the velocity distribution of AH-1G helicopter hover rotor on the rocket trajectory as an example, the numerical results are compared with Landgrebe’s predicted wake inflow model analysis results, which are in good agreement.