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首页> 外文期刊>Journal of the American Helicopter Society >Numerical Comparison of Dynamic Stall for Two-Dimensional Airfoils and an Airfoil Model in the DNW-TWG
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Numerical Comparison of Dynamic Stall for Two-Dimensional Airfoils and an Airfoil Model in the DNW-TWG

机译：DNW-TWG中二维翼型动力失速的数值比较和翼型模型

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摘要

The airfoil sections of helicopter rotors experience a wide range of flow conditions in forward flight from transonic flow on the advancing blade to subsonic flow and high angles of attack on the retreating blade. Most notably, the dynamic stall phenomenon has been a research topic for decades and various models have been introduced to predict the unsteady characteristics of the rotor blade undergoing unsteady separation. The objective of the present paper is to compare two-dimensional (2D) dynamic stall computations, suitable for airfoil design studies considering unsteady characteristics, with computational fluid dynamics simulations of the wind tunnel environment taking into account three dimensionality and wall effects. Differences between experiment and 2D computations can be partly attributed to sidewall effects, which alter the effective angle of attack at the midsection pressure measurement plane. To gain more insight into these effects, investigations are presented, which show the wind tunnel wall boundary layers and separation effects at the sidewall-airfoil junction.
机译：从前进叶片上的跨音速流到亚音速流，以及后退叶片的高攻角，直升机旋翼的机翼段在向前飞行中会经历各种流动条件。最显着的是，动态失速现象一直是数十年来的研究主题，并且已经引入了各种模型来预测经历非稳态分离的转子叶片的非稳态特性。本文的目的是比较二维（2D）动态失速计算，该计算适用于考虑非稳态特性的机翼设计研究，并考虑了三维和壁面效应，对风洞环境进行了计算流体动力学模拟。实验和2D计算之间的差异可以部分归因于侧壁效应，该效应会改变中段压力测量平面上的有效迎角。为了更深入地了解这些影响，我们进行了研究，显示了风洞壁边界层和侧壁-翼型交界处的分离效应。

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  • 来源
    《Journal of the American Helicopter Society》 |2012年第4期|p.042007.1-042007.13|共13页
  • 作者

    A. Klein; Th. Lutz; E. Kraemer; K. Richter; A. D. Gardner; A. R. M. Altmikus;

  • 作者单位

    Institute of Aerodynamics and Gas Dynamics, University of Stuttgart, Stuttgart, Germany;

    Institute of Aerodynamics and Gas Dynamics, University of Stuttgart, Stuttgart, Germany;

    Institute of Aerodynamics and Gas Dynamics, University of Stuttgart, Stuttgart, Germany;

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

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

    Aerodynamics Department ETGA Eurocopter Deutschland GmbH Munich, Germany;

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