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试验研究了直升机机身受旋翼气流干扰时的空气动力特性。试验结果证实机身阻力与旋翼前进比和桨盘载荷变化密切相关，机身升力和俯仰力矩的大小与旋翼桨盘载荷关系更大。通过对试验数据的初步分析，确定机身受旋翼尾流影响的气动干扰算式结构，利用最小二乘原理建立了简单有效的直升机机身在旋翼尾流干扰下的气动力算式，该算法可直接用于直升机气动设计和实时仿真模型中。
The aerodynamic characteristics of a helicopter fuselage interfered by the rotor airflow were studied experimentally. The test results confirm that the fuselage resistance is closely related to the rotor advance ratio and the change of the paddle load. The magnitude of the lift and pitching moment of the fuselage is more related to the load on the rotor paddle. Through the preliminary analysis of the experimental data, the aerodynamic interference formula of fuselage affected by the rotor wake is determined, and the simple and effective helicopter fuselage aerodynamic formula is established by using least squares principle. The algorithm can be directly Used in helicopter aerodynamic design and real-time simulation model.