Numerical study of head-on blade-vortex interaction noise

San-Yih Lin, Yu Fene Chen

Research output: Contribution to conferencePaper

1 Citation (Scopus)

Abstract

A numerical study is accomplished to investigate the far-field head-on blade-vortex interaction (BVI) noise. The Reynolds-averaged Navier-Stokes equations are used to simulate the phenomenon of the BVI. They are solved with the modified Osher-Chakravarthy’s finite volume scheme which is third-order accurate in space and second-order in time. The far-field noise is analyzed by the Kirchhoff’s method. Therefore only the near- and mid-field solutions are necessary to be solved precisely, as for the far field informations, they can be calculated from the near- and mid-field solutions. Comparisons of two turbulence models, the Baldwin-Lomax model and the Johnson-King model, are presented. It is demonstrated that when the free stream Mach number is lower than 0.755 approximately for NACA0012 airfoil, the Baldwin-Lomax model can have acceptable results. Numerical tests, flat plate boundary layer and NACA0012 airfoil flowfields, are presented to demonstrate the accuracy and merits of the scheme studied. During the BVI process, acoustic wave is generated and the most loud region is found below the airfoil.

Original languageEnglish
Publication statusPublished - 1997 Jan 1
Event35th Aerospace Sciences Meeting and Exhibit, 1997 - Reno, United States
Duration: 1997 Jan 61997 Jan 9

Other

Other35th Aerospace Sciences Meeting and Exhibit, 1997
CountryUnited States
CityReno
Period97-01-0697-01-09

Fingerprint

blade-vortex interaction
airfoils
Airfoils
vortex
far fields
Vortex flow
free flow
turbulence models
flat plates
Turbulence models
Mach number
Navier-Stokes equation
Navier Stokes equations
boundary layers
Navier-Stokes equations
Boundary layers
acoustic wave
plate boundary
Acoustic waves
acoustics

All Science Journal Classification (ASJC) codes

  • Space and Planetary Science
  • Aerospace Engineering

Cite this

Lin, S-Y., & Chen, Y. F. (1997). Numerical study of head-on blade-vortex interaction noise. Paper presented at 35th Aerospace Sciences Meeting and Exhibit, 1997, Reno, United States.
Lin, San-Yih ; Chen, Yu Fene. / Numerical study of head-on blade-vortex interaction noise. Paper presented at 35th Aerospace Sciences Meeting and Exhibit, 1997, Reno, United States.
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abstract = "A numerical study is accomplished to investigate the far-field head-on blade-vortex interaction (BVI) noise. The Reynolds-averaged Navier-Stokes equations are used to simulate the phenomenon of the BVI. They are solved with the modified Osher-Chakravarthy’s finite volume scheme which is third-order accurate in space and second-order in time. The far-field noise is analyzed by the Kirchhoff’s method. Therefore only the near- and mid-field solutions are necessary to be solved precisely, as for the far field informations, they can be calculated from the near- and mid-field solutions. Comparisons of two turbulence models, the Baldwin-Lomax model and the Johnson-King model, are presented. It is demonstrated that when the free stream Mach number is lower than 0.755 approximately for NACA0012 airfoil, the Baldwin-Lomax model can have acceptable results. Numerical tests, flat plate boundary layer and NACA0012 airfoil flowfields, are presented to demonstrate the accuracy and merits of the scheme studied. During the BVI process, acoustic wave is generated and the most loud region is found below the airfoil.",
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Lin, S-Y & Chen, YF 1997, 'Numerical study of head-on blade-vortex interaction noise' Paper presented at 35th Aerospace Sciences Meeting and Exhibit, 1997, Reno, United States, 97-01-06 - 97-01-09, .

Numerical study of head-on blade-vortex interaction noise. / Lin, San-Yih; Chen, Yu Fene.

1997. Paper presented at 35th Aerospace Sciences Meeting and Exhibit, 1997, Reno, United States.

Research output: Contribution to conferencePaper

TY - CONF

T1 - Numerical study of head-on blade-vortex interaction noise

AU - Lin, San-Yih

AU - Chen, Yu Fene

PY - 1997/1/1

Y1 - 1997/1/1

N2 - A numerical study is accomplished to investigate the far-field head-on blade-vortex interaction (BVI) noise. The Reynolds-averaged Navier-Stokes equations are used to simulate the phenomenon of the BVI. They are solved with the modified Osher-Chakravarthy’s finite volume scheme which is third-order accurate in space and second-order in time. The far-field noise is analyzed by the Kirchhoff’s method. Therefore only the near- and mid-field solutions are necessary to be solved precisely, as for the far field informations, they can be calculated from the near- and mid-field solutions. Comparisons of two turbulence models, the Baldwin-Lomax model and the Johnson-King model, are presented. It is demonstrated that when the free stream Mach number is lower than 0.755 approximately for NACA0012 airfoil, the Baldwin-Lomax model can have acceptable results. Numerical tests, flat plate boundary layer and NACA0012 airfoil flowfields, are presented to demonstrate the accuracy and merits of the scheme studied. During the BVI process, acoustic wave is generated and the most loud region is found below the airfoil.

AB - A numerical study is accomplished to investigate the far-field head-on blade-vortex interaction (BVI) noise. The Reynolds-averaged Navier-Stokes equations are used to simulate the phenomenon of the BVI. They are solved with the modified Osher-Chakravarthy’s finite volume scheme which is third-order accurate in space and second-order in time. The far-field noise is analyzed by the Kirchhoff’s method. Therefore only the near- and mid-field solutions are necessary to be solved precisely, as for the far field informations, they can be calculated from the near- and mid-field solutions. Comparisons of two turbulence models, the Baldwin-Lomax model and the Johnson-King model, are presented. It is demonstrated that when the free stream Mach number is lower than 0.755 approximately for NACA0012 airfoil, the Baldwin-Lomax model can have acceptable results. Numerical tests, flat plate boundary layer and NACA0012 airfoil flowfields, are presented to demonstrate the accuracy and merits of the scheme studied. During the BVI process, acoustic wave is generated and the most loud region is found below the airfoil.

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M3 - Paper

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Lin S-Y, Chen YF. Numerical study of head-on blade-vortex interaction noise. 1997. Paper presented at 35th Aerospace Sciences Meeting and Exhibit, 1997, Reno, United States.