Research on Aerodynamic Shape Optimization of Airfoils Considering Dynamic Stall Characteristics

张强; 常林森; 李春; 岳敏楠; 张万福

doi:10.19805/j.cnki.jcspe.2026.240512

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Research on Aerodynamic Shape Optimization of Airfoils Considering Dynamic Stall Characteristics

更新时间：2026-10-10

- Research on Aerodynamic Shape Optimization of Airfoils Considering Dynamic Stall Characteristics
- Chinese Journal of Power Engineering Vol. 46, Issue 1, Pages: 67-76(2026)
- 作者机构：
  
  1. 上海理工大学能源与动力工程学院,上海,200093
  2. 上海市动力工程多相流动与传热重点实验室,上海,200093
- 作者简介：
- 基金信息：
- DOI：10.19805/j.cnki.jcspe.2026.240512
  CLC：
- Online First：15 January 2026，
  
  Published：15 January 2026
- 稿件说明：
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张强,常林森,李春,岳敏楠,张万福. 考虑动态失速特性的翼型气动外形优化研究动力工程学报, 2026, 46(1): 67-76 https://doi.

org/10.19805/j.cnki.jcspe.2026.240512
张强,常林森,李春,岳敏楠,张万福. 考虑动态失速特性的翼型气动外形优化研究动力工程学报, 2026, 46(1): 67-76 https://doi. DOI： 10.19805/j.cnki.jcspe.2026.240512.

org/10.19805/j.cnki.jcspe.2026.240512 DOI：

摘要

气动外形优化方法是提高翼型气动效率及缓解动态失速的重要手段

但此方法需要多次调用精确但耗时的计算流体力学(CFD)模拟

计算成本很高。提出了一种基于代理模型的优化方法替代CFD计算

从而开展翼型动态失速特性优化。通过高斯过程回归模型构建代理模型

采用加点准则的方式不断提高模型精度

利用归一化均方根误差对代理模型进行验证

并以S809翼型为研究对象

验证该优化框架的可行性。结果表明:与基准翼型相比

优化翼型的平均阻力系数和力矩系数分别降低了32.87%和23.74%

气动性能显著提高;气动外形的改变加速了吸力面近壁流动的速度恢复

减小了边界层厚度。

Abstract

Aerodynamic shape optimization methods are important means to enhance the aerodynamic efficiency of airfoils and alleviate dynamic stall

but require repeatedly invoking precise yet time-consuming computational fluid dynamics (CFD) simulations

resulting in high computational costs. An optimization method based on surrogate model was proposed to replace CFD calculations

thereby conducting optimization of dynamic stall characteristics of airfoils. The surrogate model was constructed using the Gaussian process regression model

and the accuracy of the model was continuously improved by adopting the point addition criterion. The surrogate model was verified using the normalized root mean square error

and the feasibility of the optimization framework was verified using the S809 airfoil as the research object. Results show that compared with the baseline airfoil

the average drag coefficient and moment coefficient of the optimized airfoil are reduced by 32.87% and 23.74%

respectively

the aerodynamic performence was significantly improved. And the change in the aerodynamic shape accelerates the velocity recovery of the suction surface near the wall and reduces the boundary layer thickness.

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references

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