Design of adaptive transonic laminar airfoils using the γ-Re˜θt transition model
Design of adaptive transonic laminar airfoils using the γ-Re˜θt transition model
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DOI：
10.1016/j.ast.2015.06.027
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发表时间：
2015-10
影响因子：
5.6
通讯作者：
M. Robitaille;A. Mosahebi;E. Laurendeau
中科院分区：
文献类型：
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作者：
M. Robitaille;A. Mosahebi;E. Laurendeau
本文采用γ-Re ~ θ t模型作为过渡预测方法，研究了跨声速流型中自适应层流翼型的设计。描述了过渡模型的鲁棒求解过程，并对网格收敛性进行了研究。从模型的预测，然后比较了一套广泛的实验结果，其中包含一个变形翼型的过渡测量。结果表明，γ-Re≈θ t跃迁模型相对于形状变化的灵敏度允许其在设计框架中使用。采用多点优化策略，将该模型用于设计适合一系列流动条件的跨声速翼型。潜在的改进与自适应翼型技术的实施相关的阻力，然后仔细量化使用单点优化与多点设计翼型作为参考。考虑了结构设计约束，以获得一个现实的估计，可能通过翼型变形减少阻力使用当前的机翼结构技术。在大型公务机典型的流动条件下，相对于基线多点设计，翼梁之间的上表面部分的变形可使翼型阻力改善4.6%。
This paper examines the design of adaptive laminar airfoils in the transonic flow regime using the γ-Re˜ θ t model as a transition prediction method. A robust solution procedure for the transition model is described and a grid convergence study is presented. Predictions from the model are then compared to an extensive set of experimental results containing transition measurements on a morphing airfoil. It is shown that the sensitivity of the γ-Re˜ θ t transition model with respect to shape variations allows its use in a design framework. Using a multi-point optimization strategy, the model is then used to design transonic airfoils suitable for a range of flow conditions. The potential improvement in drag associated with the implementation of adaptive airfoil technology is then carefully quantified using single-point optimization with the multi-point designed airfoil as a reference. Structural design constraints are taken into account to obtain a realistic estimate of possible drag reduction through airfoil morphing using current wing construction technology. Airfoil drag improvements of up to 4.6% are obtained through morphing of the section of upper surface located between the wing spars with respect to the baseline multi-point design in flow conditions typical of large business jet operation.