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CLC number: V22

On-line Access: 2016-08-05

Received: 2015-11-22

Revision Accepted: 2016-01-20

Crosschecked: 2016-07-24

Cited: 4

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Citations:  Bibtex RefMan EndNote GB/T7714


Wei Huang


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Journal of Zhejiang University SCIENCE A 2016 Vol.17 No.8 P.632-645


A study of airfoil parameterization, modeling, and optimization based on the computational fluid dynamics method

Author(s):  Tian-tian Zhang, Wei Huang, Zhen-guo Wang, Li Yan

Affiliation(s):  Science and Technology on Scramjet Laboratory, of Defense Technology, Changsha 410073,

Corresponding email(s):   weihuang@nudt.edu.cn

Key Words:  Class/shape function transformation (CST), Parameterization, Numerical simulation, Response surface model, Optimization, Airfoil design

Tian-tian Zhang, Wei Huang, Zhen-guo Wang, Li Yan. A study of airfoil parameterization, modeling, and optimization based on the computational fluid dynamics method[J]. Journal of Zhejiang University Science A, 2016, 17(8): 632-645.

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author="Tian-tian Zhang, Wei Huang, Zhen-guo Wang, Li Yan",
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%T A study of airfoil parameterization, modeling, and optimization based on the computational fluid dynamics method
%A Tian-tian Zhang
%A Wei Huang
%A Zhen-guo Wang
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%DOI 10.1631/jzus.A1500308

T1 - A study of airfoil parameterization, modeling, and optimization based on the computational fluid dynamics method
A1 - Tian-tian Zhang
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A1 - Zhen-guo Wang
A1 - Li Yan
J0 - Journal of Zhejiang University Science A
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PB - Zhejiang University Press & Springer
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DOI - 10.1631/jzus.A1500308

An excellent airfoil with a high lift-to-drag ratio may decrease oil consumption and enhance the voyage. Based on NACA 0012, an improved airfoil is explored in this paper. The class/shape function transformation has been proved to be a good method for airfoil parameterization, and in this paper it is modified to improve imitation accuracy. The computational fluid dynamics method is applied to obtain numerically the aerodynamic parameters of the parameterized airfoil, and the result is proved credible by comparison with available experimental data in the open literature. A polynomial-based response surface model and the uniform Latin hypercube sampling method are employed to decrease computational cost. Finally, the nonlinear programming by quadratic Lagrangian method is utilized to modify the multi-island genetic algorithm, which has an improved optimization effect than the method used on its own. The obtained result shows that the modified class/shape function transformation method produces a better imitation of an airfoil in the nose and tail regions than the original method, and that it will satisfy the tolerance zone of the model in a wind tunnel. The response surface model based on the uniform Latin hypercube sampling method gives an accurate prediction of the lift-to-drag ratio with changes in the design variables. The numerical result of the flow around the airfoil shows reasonable agreement with the experimental data graphically and quantitatively. Ultimately, an airfoil with better capacity than the original one is acquired using the multi-island genetic algorithm based nonlinear programming by quadratic Lagrangian optimization method. The pressure contours and lift-to-drag ratio along with the attack angle have been compared with those of the original airfoil, and the results demonstrate the strength of the optimized airfoil. The process for exploring an improved airfoil through parameterization to optimization is worth referencing in future work.

The authors describe an interesting exercise of the aerodynamic optimization of a NACA0012 profile using a CST parametrization, a polynomial based response surface model as surrogate model combined with a latin hypercube sampling to reduce the computational cost and a combination of Genetic Algorithm and gradient algorithms as optimization method. The main advance proposed by the authors is a new distribution of the control points given by formula (8). This new distribution allows a better definition of the nose and tail area of the airfoil without sacrificing the accuracy in the rest of the profile.


目的:1. 比较并改善翼型参数化方法,获得设计变量少、拟合精度高的参数化方法;2. 在参数化的基础上利用数值模拟的方法获取翼型流场参数,优化并获得特定条件下升阻比最大的翼型。
创新点:1. 通过与多项式拟合方法的对比证明了类别/形状函数转换(CST)法在翼型拟合方面的优越性,并通过调整控制点分布,在不增加设计变量的基础上改善了CST方法;2. 通过建立响应面模型,利用多岛遗传算法与非线性序列二次规划法相结合的方式获得了更好的翼型优化效果。
方法:1. 利用修饰后的CST法对翼型进行参数化拟合与设计,并通过与二项式拟合法比较来验证其优越性;2. 通过数值方法对翼型周围流场进行计算并与实验结果对比,获得精确计算气动参数的仿真条件;3. 通过拉丁超立方采样获得设计变量,建立设计变量与翼型升阻比之间的响应面模型,通过多岛遗传算法与非线性序列二次规划法的结合和优化,得到一定条件下升阻比最大的翼型。
结论:1. CST法是一种优秀的参数化方法,本文的优化改善了形状函数控制点选取法则,使其对翼型头部和尾部的描述更加精确;与多项式相比,CST法可以通过更少的设计变量得到更高的拟合精度。2. 基于多岛遗传算法的非线性序列二次规划法在本文中用以优化翼型使其具有更高升阻比。优化前后翼型的比较显示,两种优化方法的结合可以得到比单独使用各优化方法更好的结果。


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