基于EFFD方法的自然层流短舱优化设计  

Natural laminar flow nacelle optimization design based on EFFD method

作　　者：何小龙[1] 白俊强[1] 夏露[1] 陈颂[1] 乔磊[1] 

机构地区：[1]西北工业大学航空学院,西安710072

出　　处：《航空动力学报》2014年第10期2311-2320,共10页Journal of Aerospace Power

基　　金：省部级重点项目

摘　　要：采用extended free-form deformation(EFFD)方法研究了自然层流(natural laminar flow,NLF)短舱的气动外形优化设计方法.使用基于Bernstein基函数的EFFD方法完成了NLF短舱剖面的参数化,利用基于k-εSST(shear stress transport)两方程湍流模型的γ-θ转捩模型进行自然转捩预测,结合EFFD、一种混合动网格方法、Kriging代理模型和改进的粒子群算法(particle swarm optimization,PSO)建立了针对NLF短舱气动外形的优化设计框架.采用该框架分别对通气NLF短舱和带动力NLF短舱进行优化设计.单独通气NLF短舱优化结果的外表面实现48%的层流,阻力系数比初始通气NLF短舱减小了0.0003.带动力NLF短舱的优化结果外表面保持了41%的层流.这些结果表明采用相关技术建立的优化设计框架在NLF短舱设计中具有一定应用价值.Aerodynamic shape optimization of natural laminar flow （NLF） nacelle was studied using extended free-form deformation （EFFD） technique. An parameterization meth- od for nacelle section based on EFFD using Bernstein base functions was implemented, γ-θtransition model coupling with κ-ε shear stress transport （SST） turbulent model was used for transition prediction. An optimization system for NLF nacelle design was established in com- bination with EFFD, a hybrid grid deformation method, Kriging surrogate model and an im- proved particle swarm optimization. Both flow-through nacelle and powered nacelle were optimized using the optimization system. Optimized flow-through nacelle maintained a laminar flow about 48% and its drag coefficient was 0. 000 3 less than initial flow-through nacelle. Powered nacelle maintained a 41% laminar flow after optimization. These results indicatethat the optimization system is applicable in NLF nacelle design.

关 键 词：自然层流短舱 气动外形优化设计 extended free-form deformation(EFFD) 转捩模型 粒子群算法(PSO) KRIGING 

分 类 号：V221.3[航空宇航科学与技术—飞行器设计]