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Effective robust design of high lift NLF airfoil under multi-parameter uncertainty

机译：多参数不确定性下高升力NLF机翼的有效鲁棒设计

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摘要

The high probability of developing shock waves and occurring separation bubbles on one or both surfaces makes it very difficult to design the high-performance transonic high lift natural-laminar-flow (NLF) airfoil at low Reynolds number. To solve this problem, a framework of effective robust design optimization (RDO) is developed based on an adjusted polynomial chaos expansion (PCE) method. The adjusted PCE method can provide accurate uncertainty quantification and have less computational cost compared with Monte Carlo simulation. The gamma-Re-theta t transition model is combined with the shear stress transport turbulence model to predict the transition region for a laminar turbulent boundary layer. The Kriging model and global optimization algorithm are integrated to optimize NLF airfoil. The result of deterministic design is proved to be ill-posed and suffering from the drastic increase of drag coefficient at off-design points. The NLF airfoil of RDO only considering Mach number uncertainty shows a lift plateau resulting from separation bubbles on the upper surface when angle of attack exceeds the design point. The NLF airfoil of RDO under both Mach number and lift coefficient uncertainty shows robust performance over a range of flight conditions. These results demonstrate that the proposed framework of RDO considering multi-parameter uncertainty can effectively solve the abovementioned design difficulty. (C) 2017 Elsevier Masson SAS. All rights reserved.
机译：在一个或两个表面上产生冲击波并出现分离气泡的可能性很高，因此很难设计出低雷诺数的高性能跨音速高升力自然层流（NLF）机翼。为了解决这个问题，基于调整后的多项式混沌扩展（PCE）方法，开发了有效的鲁棒设计优化（RDO）框架。与蒙特卡洛模拟相比，调整后的PCE方法可以提供准确的不确定性量化，并且具有较低的计算成本。将γ-Re-thet过渡模型与切应力传输湍流模型结合起来，以预测层流湍流边界层的过渡区域。集成了克里格模型和全局优化算法以优化NLF机翼。确定性设计的结果被证明是不正确的，并且在偏离设计点时受到阻力系数的急剧增加的困扰。仅考虑马赫数不确定性的RDO的NLF翼型，当攻角超过设计点时，由上表面的分离气泡导致的升程平稳。在马赫数和升力系数不确定性下，RDO的NLF机翼在一系列飞行条件下均显示出强劲的性能。这些结果表明，所提出的考虑多参数不确定性的RDO框架可以有效解决上述设计难题。 （C）2017 Elsevier Masson SAS。版权所有。

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