Turbulent boundary layer noi direct radiation a

更新时间:2023-05-25 02:12:28 阅读: 评论:0

翻译日语
商圈英文
Turbulent boundary layer noi : direct radiation at
Mach number 0.5
男人美白的方法期刊名称: Journal of Fluid Mechanics
作者: Gloerfelt, Xavier,Berland, Julien
年份: 2013年
关键词: Theoretical or Mathematical/ acoustic noi; aeroacoustics;
aerodynamics; boundary layer turbulence; compressible flow; convection; Mach number; Navier-Stokes equations; subsonic flow; supersonic flow; vortices/中文翻译成日文>licentious
turbulent boundary-layer noi; direct radiation; Mach number; aerodynamic
noi source; plane wall; direct noi contribution; spatially developing turbulent boundary layer; compressible Navier-Stokes equations; noi radiation
凛冽的拼音
characteristics; acoustic wavefronts; aerodynamic pressure; flat-plate flow;
convection effects; mean flow; source compactness; vortical events; hairpin
配饰设计培训>utuvortex; horshoe vortex; wall pressure analysis; wavenumber-frequency space;
acoustic domain; supersonic wavenumbers; convective ridge; sound emission
frequencies/ A4725M Noi (turbulence generated) A4725Q Convection and
heat transfer A4730 Rotational flow, vortices, buoyancy and other flows
involving body forces A4740D General subsonic flows A4740K Supersonic and
hypersonic flows A0230 Function theory, analysis A4710 Genera
摘要:Boundary layers constitute a fundamental source of aerodynamic noi. A turbulent boundary layer over a plane wall can provide an indirect contribution to the noi by exciting the structure and a direct noi contribution. The latter part can play a significant role even if its intensity is very low, explaining why it is difficult
love paradi 歌词
to measure. In the prent study, the aerodynamic noi generated by a spatially developing turbulent boundary layer is computed directly by solving the
compressible NavierStokes equations. This numerical experiment aims at giving some insight into the noi radiation characteristics. The acoustic wavefronts have a large wavelength and are oriented in the direction opposite to the flow. Their amplitude is only 0.7 % of the aerodynamic pressure for a flat-plate flow at Mach 0.5. The particular
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