Minimization of the Wing Airfoil Drag Coefficient Using the Optimal Control Method
Minimization of the Wing Airfoil Drag Coefficient Using the Optimal Control Method
复制标题
利用最优控制方法最小化机翼翼型阻力系数
DOI：
10.1007/s10697-006-0013-3
复制
发表时间：
2005
期刊：
影响因子：
0.9
通讯作者：
D. Abzalilov
中科院分区：
文献类型：
--
作者：
D. Abzalilov
本文考虑从多参数形式的表面速度（或压力）分布出发设计机翼翼型的问题。在扩压器区，速度下降规律由给定雷诺数下的最小阻力和无分离流动条件确定。研究了以改善机翼气动特性为目的的边界层抽吸的情况。利用最优控制理论得到了一个解决方案。
The problem of designing a wing airfoil starting from the surface velocity (or pressure) distribution, given in multi-parameter form, is considered. In the diffuser region, the velocity decrease law is determined from the conditions of minimum drag and separationless flow for a given Reynolds number. The case of boundary layer suction for the purpose of improving the aerodynamic characteristics of the airfoil is studied. A solution is obtained using optimal control theory.