基于N-S方程的翼型双设计点双目标优化设计

Bi-point/bi-objective optimization design of ailfoil using N-S equations

在使用N-S方程和尾迹面积分技术较精确地计算翼型气动阻力的基础上,对翼型进行参数化建模,应用Powell和目标组合方法讨论了翼型的双设计点双目标优化设计,并与单设计点单目标优化和单设计点双目标优化进行了对比.在给定设计条件下,2种翼型RAE2822和“类全球鹰”翼型的计算结果表明,针对翼型设计状态,合理选择目标优化函数是必要和重要的;所采用的双设计点双目标设计方法可以兼顾多种设计状态,其优化翼型相对原始翼型具有更好的压强分布,有效提高了升力系数和降低了阻力系数;相对单设计点单目标优化和单设计点双目标优化翼型也具有更高的综合气动性能.

Based on the computation of N-S equations and the technique of wake integration method, the sharp of the airfoil was paramerically modeled, the bi-point（BP）/bi-objective（BO） optimization design of ailfoil was discussed with the comparison of single-point（SP）/single-objective（SO） and single-point（SP）/bi-objective（BO） optimization. Powell method and objective function combination method was integrated. Numerical results of given airfoils（ RAE2822 and quasi-global hawk ailfoils） cases show that the BP/BO design method is compatible and effective for multiform design status and it is necessary and important to choose the objective function in the optimization method. The BP/BO optimal ailfoils have better pressure distribution to the original ones, which leads to higher coefficient of lift and lower coefficient of drag, thus results in better integral performance. The BP/BO optimal airfoils also have better integral performance to the SP/SO and the SP/BO ones.