基于目标压力分布优化的翼型反设计方法研究  

Study on Inverse Design Method of Airfoil Based on Optimizati on of Target Pressure Distribution

作　　者：李焦赞[1] 高正红[1] 詹浩[1] 

机构地区：[1]西北工业大学航空学院,西安710072

出　　处：《弹箭与制导学报》2008年第1期187-190,共4页Journal of Projectiles,Rockets,Missiles and Guidance

基　　金：航空科学基金(04A53004)资助

摘　　要：针对翼型反设计方法中目标压力分布难以给定的问题,进行了反设计方法与优化方法相结合的研究,建立了翼型反设计方法中定义目标压力分布的遗传优化模型。首先提出翼型表面压力分布参数化方法,对其进行有约束优化,获得目标压力分布,并与基于Takanashi余量修正原理的翼型反设计方法相结合,进行翼型反设计。设计结果表明这种方法是可行的。A genetic algorithm was applied to optimize target pressure distribution for inverse design method. Pressure distribution around airfoils was parameterized and the airfoil drag was minimized under constraints on lift, airfoil thickness, and other design principles. Once target pressure distribution is obtained, the corresponding airfoil geometries can be computed by an inverse design code coupled with a N- S solver. The presented results of the designed airfoil for transonic case show that the developed method is feasible.

关 键 词：目标压力分布 遗传算法 余量修正方法 反设计 

分 类 号：TJ011.3[兵器科学与技术—兵器发射理论与技术]