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为了克服传统旋翼翼型优化设计方法的不足,发展了一种基于Kriging模型与遗传算法的旋翼翼型多目标多约束气动优化设计方法。采用基于雷诺平均Navier-Stokes方程的数值模拟获得样本翼型气动性能,并建立目标函数和状态函数的Kriging模型,采用遗传算法搜索Kriging模型最小值和相应的EI(Expected Improvement)函数最大值,更新Kriging模型直至找到满足约束的最优翼型。运用加权目标函数法进行了旋翼翼型的多设计点优化设计。优化结果表明,优化后旋翼翼型在满足约束的同时,与基准旋翼翼型OA209相比:在悬停状态下,阻力系数下降了2.1%;在机动状态下,最大升力系数提高了4.2%;在前飞状态下,阻力系数在不同马赫数下均有所减小。
In order to overcome the shortcomings of traditional rotary wing airfoil optimization design methods, a multi-objective and multi-constrained aerodynamic optimization design method based on Kriging model and genetic algorithm is developed. The aerodynamic performance of the sample airfoil is obtained by numerical simulation based on the Reynolds-averaged Navier-Stokes equation, and the Kriging model of the objective function and the state function is established. The genetic algorithm is used to search the minimum of the Kriging model and the corresponding maximum value of the Expected Improvement function Kriging model until you find the optimal airfoil to meet the constraints. The multi-design point optimization design of rotor airfoil is carried out by using weighted objective function method. The optimization results show that the optimized rotor airfoils satisfy the constraints and the drag coefficient decreases by 2.1% when compared with the reference rotor airfoil OA209. Under the maneuvering condition, the maximum lift coefficient increases by 4.2% In the forward flight, the drag coefficient decreases at different Mach numbers.