面向阻力发散的CRM机翼气动优化设计  

Aerodynamic Optimization Design of CRM Wing Faced on Drag Divergence

作　　者：蒋城 刘峰博 李典 梁益华[1] JIANG Cheng;LIU Feng bo;LI Dian;LIANG Yi hua(Xi′an Aeronautics Computing Technique Research Institute,AVIC,Xi′an 710068,China)

机构地区：[1]航空工业西安航空计算技术研究所,陕西西安710068

出　　处：《航空计算技术》2018年第5期46-49,共4页Aeronautical Computing Technique

基　　金：国家某重点专项项目资助(MJ-2015-F-010)

摘　　要：为改善CRM机翼在偏离巡航点阻力系数迅速增大的问题,同时为得到更加稳定的阻力发散特性,在满足工程实际的气动约束和几何约束条件下,基于RANS方程及其离散伴随方程、FFD几何参数方法、线弹性网格变形方法以及SNOPT梯度优化算法等,对其进行单点、多权重两点以及多点优化设计。结果表明:不同优化策略下优化后机翼在主设计点处阻力系数较初始构型均有不同程度降低,经多点优化后机翼的巡航马赫数提高,且阻力发散特性的鲁棒性得以提高。In order to increase the drag coefficient of the CRM wing at a deviation from the cruising point,and look for a more stable drag divergence characteristic.Under the conditions of aerodynamic constrains and geometric constrains of engineering practice,based on the RANS equation and its discreteadjoint equation,and the FFD geometric parameterization and algebraic linear elasticity method and SNOPT gradient optimization algorithm,a single point,multi weight two points and multi points optimization design is carried out.The results show that the drag coefficient of the optimized wing at the main design point is lower than of the initial configuration under the different optimization strategies.The cruising Mach number of the wing is improved and the robustness of the resistance divergence is also improved after the multi point optimization.

关 键 词：阻力发散 离散伴随 气动优化 多点优化 

分 类 号：V212[航空宇航科学与技术—航空宇航推进理论与工程]