可变厚度机翼气动特性优化方法  

for variable thickness wing

作　　者：徐凯 段富海[1] XU Kai;DUAN Fuhai(School of Mechanical Engineering,Dalian University of Technology,Dalian 116024,China)

机构地区：[1]大连理工大学机械工程学院,辽宁大连116024

出　　处：《大连理工大学学报》2024年第4期368-375,共8页Journal of Dalian University of Technology

基　　金：国家自然科学基金资助项目(51975082)。

摘　　要：为了使飞行器在不同飞行状态下均保持良好气动特性,提出了一种可变厚度机翼气动特性优化方法.首先,以NACA0012为设计翼型,采用CST方法将翼型参数化,利用Isight集成XFoil对目标翼型优化,得到优化后翼型参数并进行气动特性分析;其次,基于优化结果,利用Fluent对翼型气动特性进行分析,得到翼型变截面厚度变化前后表面压力分布情况.结果表明,对于NACA0012翼型,在飞行马赫数为0.3、迎角为10°时,变形优化后可以使升阻比提高13.06%.In order to maintain great aerodynamic characteristics of aircraft under different flight conditions,an optimization method of aerodynamic characteristics for variable thickness wing is proposed.Firstly,using NACA0012 as the design airfoil,which is parameterized by CST method,Isight integrated XFoil is used to optimize the target airfoil.The optimized airfoil parameters are obtained and aerodynamic characteristics are analyzed.Secondly,based on the optimization results,combined with the analysis of aerodynamic characteristics of the airfoil by Fluent,the surface pressure distributions before and after the change of the variable section thickness of the airfoil are obtained.The results show that for the NACA0012 airfoil,when the flight Mach number is 0.3 and the angle of attack is 10°,the lift-drag ratio can be increased by 13.06%after deformation optimization.

关 键 词：变形机翼 CST参数化 翼型优化 气动分析 

分 类 号：V224[航空宇航科学与技术—飞行器设计]