通用飞机螺旋桨翼型多目标优化

Multi-objective optimization of propeller airfoil for general aviation aircraft

为获得具有较高气动性能、较低气动噪声的翼型,对某通用飞机螺旋桨所用RAF-6翼型进行优化设计。使用CFD/FW-H(Ffowcs Williams-Hawkings)方法对翼型进行了流场与声场数值仿真计算;其次,分别研究翼型最大厚度、最大厚度位置、后缘下弯角度与后缘下弯位置4个设计变量对其气动性能与气动噪声的影响规律;以巡航状态为设计点,以高升阻比及低气动噪声为优化目标对翼型进行多目标优化设计,获得Pareto解集。通过试验验证翼型优化后的螺旋桨拉力提高14.7%,气动噪声降低2.3 dB。

In order to obtain an airfoil with higher aerodynamic performance and lower aerodynamic noise,the RAF-6 airfoil for a general aviation aircraft propeller was optimized.The flow field and sound field of the airfoil were simulated by CFD/FW-H(Ffowcs Williams-Hawkings)method.The influence laws of four design variables,i.e.the maximum thickness,the position of the maximum thickness,the downbending angle and position of trailing edge,on its aerodynamic performance and aerodynamic noise were studied respectively.Taking the cruise state as the design point,the airfoil multi-objective optimization design was carried out with higher lift-drag ratio and lower aerodynamic noise as the optimization objectives,and the Pareto solution set was obtained.The experimental results verified that the optimized airfoil increased the propeller thrust by 14.7%and reduced the aerodynamic noise by 2.3 dB.