摘要
针对尾吊布局飞机考虑发动机干扰的机身后体减阻优化设计问题,建立了适用于复杂构型的气动外形优化设计系统。该优化设计系统采用了自由形变(FFD)参数化方法和基于紧支函数的径向基函数(RBF)动网格技术、计算流体力学(CFD)技术、Kriging代理模型以及改进的微分进化算法。利用该系统对机身后体进行了减阻优化设计,总阻力减小了2.67%。流场分析显示,阻力减小得益于优化后改变了机身后体与短舱之间流管的形状,减小了与挂架产生的不利干扰,消除了流动分离,削弱了激波强度。优化结果表明,针对尾吊布局飞机后体减阻优化设计问题,所建立的优化设计系统具有较好的实用性。
Aimed at reducing tail-mounted engine layout civil after-body drag with the interference of engines, we establish an aerodynamic optimization design system for the complex configurations. The design system is established with free formed deformation （FFD） parameterizatJon method, radial basis functions （RBF） dynamic mesh method based on compact support function, computational fluid dynamics （CFD） technology, Kriging metamodeling and improved differential evolution algorithm. The optimization design system is used in after-body drag reduction design and then a decrease of 2.67 % in the total drag is obtained. From the analysis of flow field, the change of the stream tube shape between after-body and nacelle reduces the unfavorable interference, eliminates the flow separation and weakens the shock strength, and then reduces the drag. The results show that the aerodynamic optimization design system constructed in this paper has good practicability in dealing with the tail-mounted engine layout civil after-body drag reduction problem.
出处
《航空学报》
EI
CAS
CSCD
北大核心
2014年第7期1836-1844,共9页
Acta Aeronautica et Astronautica Sinica
关键词
气动阻力
气动优化设计
尾吊布局
微分进化算法
FFD技术
径向基函数
动网格
机身后体
aerodynamic drag
aerodynamic optimization design
tail-mounted engine layout
differential evolution algo-rithm
FFD technique
radial basis functions
dynamic mesh
civil after-body
