基于混沌多项式方法的层流超临界翼型稳健设计研究

Robust design of laminar flow supercritical airfoil based on PCE method

开展层流超临界翼型稳健设计研究。针对传统的基于蒙特卡洛不确定分析方法的稳健设计系统计算量巨大、效率低下等问题,引入了混沌多项式方法,建立了新型稳健设计系统。采用RAE2822翼型稳健设计验证了设计系统的可靠性、高效性。结果表明,混沌多项式方法在保证设计精度的基础上设计效率提高了10倍左右。采用该系统进行了层流超临界翼型稳健设计研究,设计的结果表明:对于层流超临界翼型设计需要兼顾层流区长度、阻力发散特性;基于多目标稳健设计方法可以权衡设计点特性和阻力的波动特性;设计后翼型与原始翼型相比,设计点阻力减小了10cunts,阻力发散马赫数提高了0.01,在整个马赫数范围内维持了低的阻力特性。

In this paper, the robust design of laminar flow supercritical airfoil is studied. Due to the fact that the robust design system based on traditional Monte-Carlo uncertainty analysis method possesses some drawbacks, such as large computation and low efficiency, a new type of robust design system based on Polynomial Chaos Expansion(PCE) is introduced. The robust design of RAE2822 airfoil is used to test the system. Results obtained show that the design efficiency is reliable and 10 times more efficient than the traditional one. Using the system, the laminar flow supercritical airfoil is designed. The results also show that it is necessary to take into account the characteristics of the laminar flow region and the drag divergence for the design of the laminar flow supercritical airfoil. Based on the multi-objective robust design method, the characteristics of the design point and the fluctuation of the drag can be balanced, and the drag at the design point decreases 10 cunts, and the drag divergence Maher number is increased by 0.01.