Aerodynamic Shape Optimisation of Benchmark Problems Using SU2
Aerodynamic Shape Optimisation of Benchmark Problems Using SU2
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使用 SU2 基准问题的气动形状优化
DOI：
10.2514/6.2018-0412
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发表时间：
2018
期刊：
影响因子：
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通讯作者：
A. Ronch
中科院分区：
文献类型：
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作者：
Guangda Yang;A. Ronch
在本文中，结果的应用程序的开源代码，SU 2，一套基准的情况下定义的AIAA气动设计优化讨论组。采用了两种几何参数化方法，即Hicks-Henne凸块函数和自由变形。网格变形是通过求解线弹性方程来实现的。SU 2中的伴随求解器可实现高效的灵敏度分析，并使用SLSQP优化器执行基于梯度的优化。研究的第一个优化问题是NACA 0012翼型在无粘跨音速流中的阻力最小化问题，该翼型受最小厚度约束。冲击波被大大削弱并向下游移动，实现了高达83%的减阻。第二个是RAE 2822翼型在跨音速粘性流中的升力约束阻力最小化。震动消除，阻力减少38%。NACA 0012优化对参数化方法中的几个数值设置敏感，而RAE 2822优化对这些参数设置不敏感。在设计变量维度研究中也观察到相同的模式。此外，对于两个二维优化问题，非唯一的流动解决方案存在于优化的翼型。第三个问题是在亚音速、无粘流中，在定升力时使诱导阻力最小的矩形机翼的扭转优化。使用自由变形扭转参数化获得了近似椭圆的升力分布。阻力减少了大约1个计数，并且实现了改进的翼展效率。
In this paper, results are presented from the application of an open–source code, SU2, to a suite of benchmark cases defined by the AIAA Aerodynamic Design Optimisation Discussion Group. Two geometry parameterisation methods are employed, which are Hicks– Henne bump functions and Free–Form Deformation. Mesh deformation is achieved by solving linear elasticity equations. The adjoint solver within SU2 enables efficient sensitivity analysis, and gradient–based optimisation is performed using the SLSQP optimiser. The first optimisation problem studied is the drag minimisation of the NACA 0012 aerofoil in inviscid, transonic flow subject to a minimum thickness constraint. The shock wave is greatly weakened and moved downstream, achieving as much as 83% drag reduction. The second is the lift–constrained drag minimisation of the RAE 2822 aerofoil in transonic, viscous flow. The shock is eliminated, reducing drag by 38%. The NACA 0012 optimisation shows sensitivity to several numerical settings in the parameterisation approaches, whereas the RAE 2822 optimisation is insensitive to those parameter settings. The same pattern is also observed in the design variable dimensionality study. Moreover, for both two–dimensional optimisation problems, non–unique flow solutions exist on the optimised aerofoil. The third problem is the twist optimisation of a rectangular wing to minimise the induced drag at fixed lift in subsonic, inviscid flow. A nearly elliptical lift distribution is obtained using Free–Form Deformation twist parameterisation. The drag is reduced by approximately 1 count and an improved span efficiency is achieved.