多参数变弯度翼型气动优化设计方法  

Aerodynamic Optimization for Multi-parameter Variable-camber Airfoil

作　　者：王巍[1] 冯贺 刘畅 黄茹 WANG Wei;FENG He;LIU Chang;HUANG Ru(Civil Aviation College,Shenyang Aerospace University,Shenyang 110136,China;Aerospace Shenzhou Aerial Vehicle Ltd,Tianjin 300450,China)

机构地区：[1]沈阳航空航天大学民航学院,沈阳110136 [2]航天神舟飞行器有限公司,天津300450

出　　处：《科学技术与工程》2024年第3期1259-1267,共9页Science Technology and Engineering

基　　金：航空科学基金(2020Z006054002);辽宁省自然科学基金(2023-MS-243)。

摘　　要：为了获得机翼最优的气动外形,提出了一种多偏转参数与非均匀B样条结合的翼型前后缘连续偏转变形方法。以NACA3412翼型为研究实例,对翼型曲线进行参数化重构。以翼型前、后缘偏转位置和偏转角度为变化参数,模拟分析了不同变形状态对翼型气动特性的影响规律。以翼型升力系数和升阻比为优化目标,以前、后缘的偏转角度、偏转位置以及过渡段长度等六个偏转参数为设计变量,采用多目标遗传算法和ANSYS软件进行优化设计。结果表明,与基础翼型相比,优化后的变弯度翼型的升阻比提升约19.26%,升力提升约44.43%,明显改善了翼型的气动性能。Aiming at the optimal aerodynamic shape of the airfoil,a continuous deflection deformation law for the leading and trailing edge of an airfoil combining multiple-parameter deflection and B-spline was proposed.Taking NACA3412 airfoil as an example,the parametric reconstruction of airfoil curve was carried out.Numerical simulations were adopted to analysis the influence of the deflection position and angle of leading edge and trailing edge on the aerodynamic performance of the airfoil.Take the airfoil lift-to-drag ratio and lift coefficient as the optimization targets,and with six deflection parameters,including leading edge deflection angle,leading edge deflection position,leading edge transition section length,trailing edge deflection angle,trailing edge deflection position and trailing edge transition section length as the design variables,the multi-objective genetic algorithm NSGA-Ⅱ,and ANSYS software were used to optimize the variable-camber airfoil.Compared with the basic airfoil,the lift-drag ratio of the optimized variable-camber airfoil was increased by more than 19.26%while the lift coefficient was increased by more than 44.43%.

关 键 词：变弯度翼型 前后缘偏转 非均匀B样条 非支配排序遗传算法 气动特性 

分 类 号：V224[航空宇航科学与技术—飞行器设计]