高升阻比自然层流翼型多点/多目标优化设计  

Multi-point/objective optimization design of high lift-to-drag ratio for NLF airfoils

作　　者：邓磊[1] 乔志德[1] 杨旭东[1] 熊俊涛[2] 

机构地区：[1]西北工业大学翼型、叶栅空气动力学国家级重点实验室,陕西西安710072 [2]机械与航空与太空工程系,加州大学欧文分校,CA92697-3975

出　　处：《空气动力学学报》2011年第3期330-335,共6页Acta Aerodynamica Sinica

基　　金：国家自然科学基金(90605004)

摘　　要：研究并发展了一套进行高升阻比自然层流翼型多设计点/多设计目标的优化设计方法。为减少设计中的计算量,使用了XFOIL程序进行流场计算。使用基于响应面方法的优化方法进行最优化计算,并使用了不含二阶交叉项的二阶多项式模型作为响应面模型,大大减少了构造模型所需的试验次数,使进行更多设计变量和多点设计成为可能。试验点的选择满足D-优化准则。研究了设计点及目标函数的选择,进行了单点/单目标及多点/多目标的设计,结果表明:多点/多目标设计可以很好的改善单点设计中非设计点性能变差的缺点,设计结果有工程实用价值。A Multi-Point/Objective Optimization design approach of high lift-to-drag ratios for Natural Laminar Airfoils is developed.XFOIL code is used to calculate pressure distribution to reduce the computation cost.The numerical optimization is based on Response Surface Methodology and the RS model is reduced quadratic polynomials without the 2-order cross items to reduce the experiment times in constructing RS models.The set of candidate design points in design space is selected to satisfy D-optimality.Multi Point/Objective designs are performed based on the analysis of Single-Point/Objective design results.The results indicate that Multi-Point/Objective design improves the overall performance of the design with respect to the Single-Point design.

关 键 词：高升阻比 自然层流翼型 多目标设计 优化设计 响应面方法 

分 类 号：V211.412[航空宇航科学与技术—航空宇航推进理论与工程]