基于共轭方程法的跨声速机翼阻力优化设计  

Drag-reduction design of transonice wing based on adjoint method

作　　者：张野平[1] 段卓毅[1] 张彦军[1] 

机构地区：[1]西安飞机设计研究所,陕西西安710089

出　　处：《空气动力学学报》2012年第2期162-168,共7页Acta Aerodynamica Sinica

摘　　要：机翼的气动特性从根本上决定了飞机巡航状态下的气动特性,经过良好设计的机翼会明显地提升全机的气动特性。连续共轭方程方法由于其求解梯度的计算量与设计变量数目无关,可以对复杂构型进行有效的优化设计。本文采用连续共轭方程方法对粘性条件下的机翼气动外形进行了优化设计。采用有限体积法进行流动控制方程和共轭方程的数值空间离散,多步Runge-Kutta方法进行时间推进,对于某三维机翼进行了有效的气动优化设计。The aerodynamic characteristics under the cruise condition of the whole configuration will benefit from well-designed wing. Continuous adjoint method can be used to complex configuration because the computation of the sensitivity derivatives of cost function with respect to design variables is nearly independ- ent with the number of design variables. Based on the adjoint method, the problem of drag minimization of wing with viscosity is studied in present paper. The flow control equation and the adjoint equation are solved numerically with a finite volume fourth-order-accurate compact scheme for spatial discretization and Runge Kutta integration for time advancement. Finally, an effective three-dimensional wing optimization aiming at some important project is carried out in this paper.

关 键 词：跨声速机翼 阻力优化 共轭方程法 

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]