基于Euler方程的三维机翼厚度与扭角优化设计  

Optimization design of wing's thickness and twist angle using Euler equations

作　　者：李岩[1] 朱自强[1] 王晓璐[1] 陈泽民[1] 

机构地区：[1]北京航空航天大学航空科学与工程学院,北京100083

出　　处：《北京航空航天大学学报》2007年第3期269-272,277,共5页Journal of Beijing University of Aeronautics and Astronautics

基　　金：国家自然科学基金资助项目(10472013);航空科学基金资助项目(04A51044)

摘　　要：使用Euler方程作为流场解算器,结合Powell算法,讨论了在确定的机翼平面形状和翼型的条件下,以最大升阻比为目标的三维机翼截面翼型最大厚度与扭角的优化设计.设计中以机翼沿展向0.1,0.2,0.3,0.8,1.0倍半展长的翼剖面的厚度作为优化控制量,再选取翼梢剖面的扭角增量为第6个控制量,对机翼作了数值优化设计计算,得到了在亚音速时具有相对较大升阻比的机翼其厚度及扭角的优化分布.针对Lockheed-AFOSR Wing B的亚临界和超临界算例结果表明,厚度的非线性分布和负的扭角会改善机翼流场的流动状态,使机翼的升阻比得到提高,优化设计方法是可行的.With the goal of maximizing lift-to-drag ratio, the optimization of three-dimensional wing＇s section thickness and twist angle is discussed. Euler equations as flow field sovler and Powell method are used as design tools, and the wing＇s aspect shape and airfoil are fixed. The thicknesses of wing sections on the semiwingspan relative position of 0.1, 0.2, 0.3, 0.8, 1.0, with the additional twist angle are chosen as the optimal control factors. The distribution of wing＇s thickness and twist angle is obtained on the subsonic conditions with relative high lift-to-drag. The subcritical and supercritical computation of Lockheed-AFOSR wing B cases show that nonlinear distribution of thickness and negative twist angle could ameliorate the condition of flow field around the wing, which leads to higher lift-to-drag ratio, the optimization method is effective.

关 键 词：机翼设计 优化设计 EULER方程 

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]