考虑螺旋桨滑流影响的机翼气动优化设计
收稿日期: 2013-12-09
修回日期: 2014-04-08
网络出版日期: 2014-05-01
基金资助
工信部重大专项(MODERN ARK700型涡桨支线飞机)
Aerodynamic Optimization Design of Wing Under the Interaction of Propeller Slipstream
Received date: 2013-12-09
Revised date: 2014-04-08
Online published: 2014-05-01
Supported by
MIIT Special Item (MODERN ARK700 Turboprop Regional Aircraft)
涡桨飞机的机翼、短舱等部件在滑流作用下周围的流场特性与无滑流状态下截然不同.所以,应该在涡桨飞机的机翼气动设计过程中考虑螺旋桨滑流的影响,从而使得机翼在真实飞行时滑流作用下表现出更好的气动特性.采用基于雷诺平均Navier-Stokes方程的多重参考坐标系(MRF)方法对螺旋桨滑流进行高精度准定常数值模拟,通过自由变形(FFD)技术实现螺旋桨飞机机翼的参数化构建,应用径向基函数(RBF)插值的动网格技术进行网格自动生成,获得样本机翼在滑流影响下的气动数据后,建立目标函数和状态函数的Kriging代理模型,结合随机权重粒子群优化(PSO)算法、Kriging代理模型和对应的EI(Expected Improvement)函数加点准则进行加样本点以及代理模型重建,从而建立滑流影响下机翼气动优化设计系统.使用该系统对某型螺旋桨飞机进行了滑流影响下的优化设计,结果表明,优化后的构型机翼和短舱在巡航状态下减阻达3.98 counts,升阻比提高了3.325%.因此,建立的考虑滑流影响下的机翼优化设计方法是可行的.
徐家宽 , 白俊强 , 黄江涛 , 乔磊 , 董建鸿 , 雷武涛 . 考虑螺旋桨滑流影响的机翼气动优化设计[J]. 航空学报, 2014 , 35(11) : 2910 -2920 . DOI: 10.7527/S1000-6893.2014.0044
The propeller slipstream effects usually create large difference to the flow field around wings, nacelles and other parts of turboprop aircraft compared with no slipstream effect. Thus, the slipstream effects should be taken into account in aerodynamic design of wings, leading to better aerodynamic characteristics under real flying condition which includes slipstream effects. Propeller slipstream is simulated using multiple reference frames (MRF) quasi-steady method based on Reynolds-averaged Navier-Stokes equations. Free form deformation (FFD) technology is used for parameterization of wings. A grid deformation method based on radial basis functions (RBF) interpolation is embedded in optimization for rapid grid regeneration. After the aerodynamic data of wing samples is obtained, a Kriging surrogate model is trained with these original samples and iteratively improved with EI (Expected Improvement) through optimization. Combining random weighted particle swarm optimization (PSO) algorithm with aforementioned methods, the optimization system is established. The optimization design result of a certain turboprop aircraft using this optimization system indicates that the wing and nacelle of the optimized configuration have a drag reduction of 3.98 counts and lift-drag ratio increase by 3.325% in cruising state. Therefore, the numerical method and the optimization system used are practical and valuable for wing design under slipstream effects.
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