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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
The aerodynamic interference of the rotor / fuselage is calculated using an advanced free-fall analysis method. The method is based on the second-order lift-line model of the blade, the full freewheeling model of the rotor, the source facial element model of the fuselage and the trim model of the rotor. By iterating the induced velocity of the rotor / wake on the fuselage and Fuselage in the plane of the propeller, wake the positioning point of the induction rate, the formation of a fully coupled comprehensive analysis model. In this model, a close vortex / surface perturbation model is built to account for the effect of the fuselage on the wake distortion using the “numerical solution-analytic solution matching” approach. As an example, the steady and unsteady pressure distributions and aerodynamic loads on the rotor / fuselage combined body were calculated and compared with the experimental results, which shows the effectiveness of the proposed method