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Influence of Steady Pitch Rate on 2-D Airfoil Aerodynamic Characteristics at Incidence

机译：稳定俯仰率对入射时二维翼型气动特性的影响

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摘要

An investigation of steady pitch rate effects on nonlinear dependencies of 2-D airfoil aerodynamic loads at high angles of attack was undertaken. The linearized thin airfoil theory results with account of flow separation using Kirchhoff s zone of constant pressure were compared with numerical results from XFOIL. For numerical calculations the approximate concept of pitch induced curved airfoil shapes was used. It was found that the steady pitch rate effects have considerable influence on the development of the airfoil upper surface flow separation. It is essential to take into account not only the pitch rate value but the position of the rotation center also. The analytical and numerical estimations of pitch rotary derivatives C_(N_q) and C_(m_q) were obtained. The flow separation effects result in considerable nonlinear variations of these derivatives at high angles of attack. The results presented here are for a steady-state pitching motion, and so do not take into account any time-history effects. However, by establishing a static relationship between pitch rate and separation point position, this analysis provides the necessary basis for modeling the effects of the pure pitch component on dynamic stall of oscillating airfoils using (for example) the state-space methodology described in [6].
机译：进行了稳定俯仰角速度对高迎角下二维机翼气动载荷非线性相关性影响的研究。将使用克希霍夫恒压区进行流动分离的线性薄翼型理论结果与XFOIL的数值结果进行了比较。为了进行数值计算，使用了俯仰引起的弯曲翼型形状的近似概念。发现稳定的桨距率效应对机翼上表面流分离的发展具有相当大的影响。不仅要考虑俯仰率值，而且还要考虑旋转中心的位置。得到了螺距旋转导数C_（N_q）和C_（m_q）的解析和数值估计。流动分离效应导致这些导数在大迎角下发生相当大的非线性变化。此处给出的结果是针对稳态俯仰运动的，因此不考虑任何时间历史的影响。然而，通过建立俯仰率和分离点位置之间的静态关系，该分析提供了必要的基础，以使用[6]中描述的状态空间方法对纯俯仰分量对振荡翼型的动态失速进行建模。 ]。

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  • 来源
    《Journal of Aircraft》 |2006年第5期|p.1552-1555|共4页
  • 作者

    A. Khrabrov; D. Greenwell;

  • 作者单位

    Central Aerohydrodynamics Institute (TsAGI), 140180, Zhukovsky, Russia;

  • 收录信息 美国《科学引文索引》(SCI);美国《工程索引》(EI);
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类 航空;
  • 关键词

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