飞行器翼型多目标优化设计  

Multiobjective Optimization Design for Aircraft Airfoil

作　　者：李自启 万俊明 万芩 梁栋 Li Ziqi;Wan Junming;Wan Qin;Liang Dong(AVIC Hongdu,Nanchang,Jiangxi,330024)

机构地区：[1]中航工业洪都,江西南昌330024

出　　处：《教练机》2025年第1期12-16,共5页Trainer

基　　金：江西省重大科技研发专项(20203ABC28W002);航空科学基金(2019ZA066002)。

摘　　要：依据飞行器的翼型设计要求,采用CST翼型参数化方法和基于Pareto集的多目标遗传算法,设计了厚度为18%的翼根翼型和12%的翼梢翼型。设计的主要原则是减小基准翼型的力矩,并且保持巡航状态下的升阻比和最大升力系数。数值计算和风洞试验不仅验证了所设计翼型全动特性合理性,而且证明该设计方法适合用于工程实际中的低速翼型设计。According to the airfoil design requirements of aircraft,a preliminary design of the wing-root airfoil with a thickness of 18%and the wing-tip airfoil with a thickness of 12%is carried out by using the CST airfoil parameterization method and the multi-objective genetic algorithm based on Pareto set.The main principle of the design is to reduce the moment of the reference airfoil while maintaining the lift-drag ratio and the maximum lift coefficient in cruise state.Numerical calculations and wind tunnel tests not only verified the rationality of the all-moving characteristics of the designed airfoil,but also demonstrated that this design methodology is applicable to low-speed airfoil design in engineering practice.

关 键 词：翼型设计 飞行器 多目标优化 遗传算法 翼型参数化 

分 类 号：V224[航空宇航科学与技术—飞行器设计]