...
  • 主题
高级搜索  >
历史搜索 清空历史
首页> 外文期刊>Journal of the American Helicopter Society >Prediction of Rotorcraft Broadband Trailing-Edge Noise and Parameter Sensitivity Study
【24h】

Prediction of Rotorcraft Broadband Trailing-Edge Noise and Parameter Sensitivity Study

机译：旋翼飞机宽带后辐射噪声和参数灵敏度研究预测

获取原文
获取原文并翻译 | 示例
           
页面导航
  • 摘要
  • 著录项
  • 相似文献
  • 相关主题

摘要

This paper investigates the effects of rotorcraft design and operating parameters on trailing-edge noise. A rotor trailing-edge noise prediction method is first developed where the aerodynamics and the turbulence wall pressure spectrum near the trailing edge on airfoils are predicted by a combination of the standard blade element momentum theory, a viscous boundary-layer panel method, and a recently developed empirical wall pressure spectrum model. The coordinate transformations are combined with the Amiet model to predict far-field noise. Compared to experimental data, the validation of this method demonstrates its advantages and validity for airfoil and rotorcraft broadband noise predictions. Then, this method is used to study the effects of rotorcraft design and operating parameters on rotor trailing-edge noise. It is found that helicopter broadband noise scales with the 4.5th to 5.0th power of the tip Mach number in which the range is determined by the typical helicopter collective pitch angle in operation. Detailed trend analyses of noise levels as a function of frequency are presented in terms of the collective pitch angle, twist angle, rotor solidity, rotor radius, disk loading, and number of blades. It is found that the collective pitch angle, twist angle, and chord length make noticeable impacts on low- and midfrequency noise. Finally, a semianalytic model is presented to predict the directivity and geometric attenuation of rotor trailing-edge noise.
机译：本文调查了旋翼设计和操作参数对后缘噪声的影响。首先开发转子后缘噪声预测方法，其中通过标准刀片元件动量理论，粘性边界层方法和最近的壁箔上的后缘上的空气动力学和湍流壁压力谱预测。开发了经验壁压谱模型。坐标变换与亚岛模型相结合以预测远场噪声。与实验数据相比，该方法的验证证明了翼型和旋翼飞机宽带噪声预测的优点和有效性。然后，该方法用于研究旋翼机设计和操作参数对转子后边缘噪声的影响。发现直升机宽带噪声尺度与尖端马赫数的4.5到5.0功率，其中通过操作中的典型直升机集体螺距角度确定范围。根据频率函数的详细趋势分析是以集体俯仰角，扭曲角度，转子固定，转子半径，磁盘装载和叶片数而言。发现集体俯仰角，扭转角度，曲线长度对低和中频噪声产生显着的影响。最后，提出了半类模型以预测转子后缘噪声的方向性和几何衰减。

著录项

  • 来源
    《Journal of the American Helicopter Society》 |2020年第4期|042006.1-042006.14|共14页
  • 作者

    Sicheng (Kevin) Li; Seongkyu Lee;

  • 作者单位

    Department of Mechanical and Aerospace Engineering University of California Davis CA;

    Department of Mechanical and Aerospace Engineering University of California Davis CA;

  • 收录信息
  • 原文格式 PDF
  • 正文语种 eng
  • 中图分类
  • 关键词

相似文献

  • 外文文献
  • 中文文献
  • 专利
获取原文

客服邮箱：kefu@zhangqiaokeyan.com

京公网安备：11010802029741号 ICP备案号：京ICP备15016152号-6 六维联合信息科技 (北京) 有限公司©版权所有

  • 客服微信

  • 服务号