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Quadrupole Corrections for the Permeable-Surface Ffowcs Williams-Hawkings Equation

机译:渗透表面Ffowcs Williams-Hawkings方程的四极校正

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摘要

This paper focuses on the spurious noise of the Ffowcs Williams and Hawkings equation with a permeable integral surface, which is now commonly used in far-field noise prediction for computational aeroacoustics methodologies. Spurious noise arises in the surface integral terms as an adverse effect of truncating a computational domain resolved for the quadrupole sources so that hydrodynamic fluctuations pass through the integral surface with mean flow. First, the quadrupole contribution is reformulated in the form of surface integrals for additive correction by introducing a frozen turbulence assumption for uniform mean flow. The math formulation is verified for simple convecting vortices. The derived formulation is then extended to nonuniform convection for locally subsonic flow. By adding the correction to the conventional Ffowcs Williams and Hawkings surface integrals, spurious noise is suppressed in two-dimensional wake flow. In a three-dimensional turbulent jet-noise simulation, the proposed correction, extended to nonuniform convection, is demonstrated to reduce the dependence of the prediction on the streamwise end-cap location of the integral surface. The present method requires no tunable parameters, with only a minimal additional cost compared to the conventional permeable-surface integrals in the far-field noise computation.
机译:本文关注具有可渗透积分表面的Ffowcs Williams和Hawkings方程的杂散噪声,该方程现在常用于计算航空声学方法学的远场噪声预测中。杂散噪声以表面积分形式出现,这是对为四极杆源解析的计算域进行截断的不利影响,因此流体动力波动会以平均流量通过积分表面。首先,通过引入冻结湍流假设来获得均匀均流,以表面积分的形式将四极子贡献重新公式化。对简单的对流涡流验证了数学公式。然后将导出的公式扩展到局部亚音速流的非均匀对流。通过对常规的Ffowcs Williams和Hawkings表面积分进行校正,可以抑制二维尾流中的杂散噪声。在三维湍流射流噪声模拟中,拟议的校正扩展到非均匀对流,证明可以减少预测对整体表面的流向端盖位置的依赖性。与远场噪声计算中的常规可渗透表面积分相比,本方法不需要可调参数,而仅具有最小的附加成本。

著录项

  • 来源
    《AIAA Journal》 |2017年第7期|2307-2320|共14页
  • 作者单位

    Japan Aerosp Explorat Agcy, Aeronaut Technol Directorate, Tokyo 1828522, Japan;

    Japan Aerosp Explorat Agcy, Aeronaut Technol Directorate, Tokyo 1828522, Japan;

    Japan Aerosp Explorat Agcy, Aeronaut Technol Directorate, Tokyo 1828522, Japan;

    Adv Sci & Intelligence Res Inst Corp, Sci Engn Div, Tokyo 1010047, Japan;

  • 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
  • 关键词

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