基于模型试验的旋翼/机身气动干扰经验算式

An empirical algorithm of aerodynamic interaction effects of rotor wake on fuselage for helicopter based on model experiments

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 interaction effects of rotor wake on fuselage for helicopter were researched with experimental method. The results from experiment have proved that for the drag of fuselage the effect of rotor airflow is closely in connection with advanced ratio μ and disk loading p , while for the thrust and pitch moment of fuselage the disk loading plays more important role. The construction of a simple and effective computing algorithm about aerodynamic interaction were determined based on prelimiminary analysis of experimental data. The algorithm were derived from the measured data by adapting least square method.The simple and practical algorithm can be directly used in the design of aerodynamics and realtime simulation for helicopter.