【摘要】 应用先进的自由尾迹分析方法 ,对旋翼 /机身的气动干扰进行了计算。该方法建立在桨叶的二阶升力线模型、旋翼的全展自由尾迹模型、机身的源面元模型、旋翼的配平模型的基础上 ,通过迭代旋翼 /尾迹在机身上的诱导速度和机身在桨盘平面、尾迹定位点的诱导速度 ,形成一个全耦合的综合分析模型。在该模型中 ,采用“数值解 -分析解匹配”的方法建立了一贴近涡 /面干扰模型来计入机身对尾迹畸变的影响。作为算例 ,分别计算了旋翼 /机身组合状态机身上的定常、非定常压强分布和气动载荷 ,并与实验结果进行了对比 ,表明了本文方法的有效性更多还原

【Abstract】 Calculations are carried out for the aerodynamic interaction between helicopter rotor and fuselage by using the advanced free wake analysis. This method is based on the blade second order lifting line model, the full span free wake model, panel model for the fuselage and rotor trim model. By iterating induced velocities on the fuselage surface caused by rotor/wake and those on the rotor plane/wake caused by fuselage, a comprehensive analytical model is established. In this model, a close vortex/surface interaction mo del is used to incorporate the influence of fuselage on the distortion of rotor wake by using “analytical numerical matching method”. As numerical examples, calculations are carried out for steady and unsteady pressure distribution, as well as the aerodynamic airloads acted on the fuselage in an combined rotor/fuselage configuration. The effect of the method is shown by comparison of numerical results with available experimental data.[KH3/4D]更多还原