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为了改善二元可变后缘翼型在外界条件变化时的气动稳定性,提出了一种考虑不确定性的鲁棒性优化方法.在类别形状函数变换(CST)方法的基础上,建立了二元可变后缘翼型的参数化模型.探讨了确定性优化方法与鲁棒性优化方法的区别.充分考虑翼型几何形状和来流马赫数的不确定性,进行了最大化升阻比均值、最小化升阻比标准差的鲁棒优化设计.对于优化后的可变后缘翼型,计算了变形所需的驱动能.结果表明:鲁棒性优化方法在提升翼型气动性能的同时降低了该性能对来流马赫数的敏感度,鲁棒性优化翼型所需的驱动能有所减少.
In order to improve the aerodynamic stability of binary variable trailing edge airfoils under changing external conditions, a robust optimization method considering uncertainty is proposed. Based on the CST method, Binary variable trailing edge airfoil parameterization model.The difference between the deterministic optimization method and the robust optimization method is discussed.With full consideration of the airfoil geometry and the uncertainty of incoming Mach number, Than the average, and minimize the standard deviation of the drag-and-drag ratio.For the variable variable trailing edge airfoil, the driving energy required for the deformation is calculated.The results show that the robust optimization method can improve the aerodynamic performance of the airfoil While reducing the sensitivity of this property to the Mach-number of incoming traffic, robustness reduces the drive required to optimize the airfoil.