Robust Airfoil Optimization with Multi-objective Estimation of Distribution Algorithm

A transonic airfoil designed by means of classical point-optimization may result in its dramatically inferior performance under off-design conditious. To overcome this shortcoming, robust design is proposed to fred out the optimal profile of an airfoil to maintain its performance in an uncertain environment. The robust airfoil optimization is aimed to minimize mean values and variances of drag coefficients while satisfying the lift and thickness constraints over a range of Maeb numbers. A multi-objective estimation of distribution algorithm is applied to the robust airfoil optimization on the base of the RAE2822 benchmark airfoil. The shape of the airfoil is obtained through superposing ten Hick-Heune shape functions upon the benchmark airfoil. A set of design points is selected according to a uniform design table for aerodynamic evaluation. A Kriging model of drag coefficient is coustrueted with those points to reduce eumputing costs. Over the Maeh range fi'om 0.7 to 0.8, the airfoil generated by the robust optimization has a configuration characterized by supercritical airfoil with low drag coefficients. The small fluctuation in its drag coefficients means that the performance of the robust airfoil is insensitive to variation of Mach number.

作 者： Zhong Xiaoping Ding Jifeng Li Weiji Zhang Yong   作者單位： Zhong Xiaoping,Li Weiji(School of Aeronautics, Northwestern Polytechnical University, Xi 'an 710072, China)

Ding Jifeng(China Space Technology Research Institute, Beijing 100083, China)

Zhang Yong(China Aerodynamics Research and Development Center, Mianyang 621000, China) 

刊 名： 中國航空學(xué)報(英文版)  ISTIC 英文刊名： CHINESE JOURNAL OF AERONAUTICS  年，卷(期)： 2008 21(4)  分類號： V2  關(guān)鍵詞： airfoil robust design   multi-objective estimation of distribution algorithm   uncertain environment   drag   fluctuation  

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