基于伴随方程和自由变形技术的跨声速机翼气动设计方法研究  

Transonic wing aerodynamic design based on continuous adjoint method and free form deform technique

作　　者：白俊强[1] 陈颂[1] 华俊 孙智伟[1] 黄江涛[3] 

机构地区：[1]西北工业大学航空学院,陕西西安710072 [2]中国航空研究院,北京100012 [3]中国空气动力研究与发展中心,四川绵阳621000

出　　处：《空气动力学学报》2014年第6期820-826,833,共8页Acta Aerodynamica Sinica

基　　金：973计划大型客机减阻机理和方法研究(2014CB744804)

摘　　要：将连续伴随方程法与自由变形技术(Free Form Deform-FFD)相结合开展了跨声速机翼气动外形优化设计方法研究。采用Bernstein基函数建立了空间FFD参数化方法,并应用基于控制理论的连续伴随方程方法建立了目标函数对于待优化几何外形的梯度求解模式,将几何外形参数化方法、连续伴随方法以及CFD数值模拟技术相结合,研究、构建了适合跨声速机翼的气动外形优化设计系统。利用该系统对ONERA M6机翼及某型民用客机机翼进行了气动减阻设计,算例验证表明该方法应用于跨声速机翼气动减阻设计效果明显,并且能较好的保持几何表面连续性和光滑性。The approach of transonic wing aerodynamic design based on the combination of continuous adjoint method with free form deform （FFD） technique has been presented. Bernstein basis function has been chosen to establish the FFD parameterization of arbitrary spatial property to overcome the disadvantages of discontinuity or unsmoothness by the bump function method or the B-spline approach. Besides, the scheme to compute the sensitivity of aerodynamic objective function respecting to geometrical shape has been established using the continuous adjoint method based on control theory, in which the sensitivity computation of all the design variables would cost one flow field computation and one adioint field computation. Combined with torsional spring mesh deformation technique, FFD geometric parameterization, continuous adjoint method and computational fluid dynamics have been integrated to establish a design system for transonic wing aerodynamic configuration aimmed at drag reduction, which is good at both efficiency and rohustness. This system has been testified with optimization design cases of ONERA M6 wing and a typical large civil jet wing, the results of which have shown that this method is of good feasibility and efficiency in aerodynamic optimization design for drag reduction. Moreover, the results have shown that this method is of good capability of conserving the geometry continuity and smoothness.

关 键 词：气动设计 伴随方程 自由变形 跨声速机翼 

分 类 号：V211.3[航空宇航科学与技术—航空宇航推进理论与工程] TP273[自动化与计算机技术—检测技术与自动化装置]