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Deployable Vortex Generator Dynamic Stall Alleviation through Experimental and Numerical Investigations

机译：通过实验和数值研究缓解可展开涡流发生器的动态失速

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摘要

The flow over an OA209 airfoil subjected to a sinusoidal pitching motion under dynamic stall conditions and equipped with an innovative deployable vortex generator actuator inducing stall control is experimentally and numerically investigated. Pressure and time-resolved particle image velocimetry measurements allow a detailed comparison to be performed between clean and controlled cases, including separation point detection and proper orthogonal decomposition analysis. Along with wind tunnel testing, numerical simulations are performed by solving the unsteady Reynolds-averaged Navier-Stokes equations with the ONERA elsA code. Computations are successfully compared to the experimental reference and bring further understanding of the deployable vortex generator actuation.
机译：实验和数值研究了在动态失速条件下经受正弦俯仰运动并配备有创新的可展开涡流发生器致动器以引起失速控制的OA209翼型上的流动。压力和时间分辨的颗粒图像测速仪测量允许在干净和受控的情况下进行详细的比较，包括分离点检测和适当的正交分解分析。除风洞测试外，还通过使用ONERA elsA代码求解不稳定的雷诺平均Navier-Stokes方程进行数值模拟。计算成功地与实验参考进行了比较，并进一步理解了可展开涡流发生器的致动。

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  • 来源
    《Journal of the American Helicopter Society》 |2013年第3期|032005.1-032005.13|共13页
  • 作者

    G. Joubert; A. Le Pape; B. Heine; S. Huberson;

  • 作者单位

    Applied Aerodynamics Department ONERA-The French Aerospace Lab Meudon Cedex, France;

    Applied Aerodynamics Department ONERA-The French Aerospace Lab Meudon Cedex, France;

    Institute of Aerodynamics and Flow Technology, German Aerospace Center (DLR), Goettingen, Germany;

    Institut P' Universite de Poitiers, CNRS Poitiers, France;

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