Aeroelastic Optimization of a Morphing 2D Shock Control Bump
Aeroelastic Optimization of a Morphing 2D Shock Control Bump
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DOI：
10.2514/6.2012-1577
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发表时间：
2012-04
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影响因子：
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通讯作者：
Oliver Rhodes;M. Santer
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文献类型：
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作者：
Oliver Rhodes;M. Santer
本文采用可展开冲击控制凸点作为变形结构，研究了RAE2822翼型的跨声速冲击控制。在最小化阻力的前提下，找到了凸起的最佳位置和形状。结构变形是通过优化器控制载荷实现的，受材料限制。系统的结构化网格生成器能够在边界层和凹凸区域进行细化，生成高质量的CFD分析网格。静态气动弹性以结构模型和气动模型之间的弱耦合形式存在。减少4.2%的阻力是实现与凹凸部署，与几何形状返回到原来的翼型，当驱动被删除。
This paper investigates transonic shock control on the RAE2822 airfoil using a deployable shock control bump designed as a morphing structure. The optimal location and shape of the bump are found with respect to minimizing drag. Structural morphing is achieved via optimizer controlled loads, constrained to respect material limitations. A systematic structured mesh generator, capable of refinement in the boundary layer and bump region, is used to generate grids of high quality for CFD analysis. Static aeroelasticity is included in the form of a weak coupling between structural and aerodynamic models. A drag reduction of 4.2 % is achieved with the bump deployed, with the geometry returning to that of the original airfoil when actuation is removed.