Numerical study on transonic blade-vortex interaction

Flowfield analysis

San-Yih Lin, Yan Shin Chin

Research output: Contribution to conferencePaper

1 Citation (Scopus)

Abstract

Numerical investigations of aerodynamic sound generation due to transonic blade-vortex interaction were performed numerically. The numerical method is based on a third-order upwind finite volume scheme in space and a second-order explicit Runge-Kutta scheme in time. A standard transonic blade vortex interaction is presented to demonstrate two dominant sound waves, transonic and compressible waves. The fluctuation dilatation and correlation of the dilatation are presented to identify these two significant sound waves that travel upstream. Three unsteady shock wave motions, types A, B and C identified by Tijdeman, were simulated by changing the physical parameters, such as Mach number, vortex strength, and initial position of the vortex.

Original languageEnglish
Publication statusPublished - 1995 Jan 1
Event33rd Aerospace Sciences Meeting and Exhibit, 1995 - Reno, United States
Duration: 1995 Jan 91995 Jan 12

Other

Other33rd Aerospace Sciences Meeting and Exhibit, 1995
CountryUnited States
CityReno
Period95-01-0995-01-12

Fingerprint

blade-vortex interaction
transonic flow
vortex
Vortex flow
sound waves
Acoustic waves
vortices
aerodynamics
Mach number
upstream
travel
shock waves
shock wave
Shock waves
numerical method
Numerical methods
Aerodynamics
acoustics
analysis
sound

All Science Journal Classification (ASJC) codes

  • Space and Planetary Science
  • Aerospace Engineering

Cite this

Lin, S-Y., & Chin, Y. S. (1995). Numerical study on transonic blade-vortex interaction: Flowfield analysis. Paper presented at 33rd Aerospace Sciences Meeting and Exhibit, 1995, Reno, United States.
Lin, San-Yih ; Chin, Yan Shin. / Numerical study on transonic blade-vortex interaction : Flowfield analysis. Paper presented at 33rd Aerospace Sciences Meeting and Exhibit, 1995, Reno, United States.
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Lin, S-Y & Chin, YS 1995, 'Numerical study on transonic blade-vortex interaction: Flowfield analysis' Paper presented at 33rd Aerospace Sciences Meeting and Exhibit, 1995, Reno, United States, 95-01-09 - 95-01-12, .

Numerical study on transonic blade-vortex interaction : Flowfield analysis. / Lin, San-Yih; Chin, Yan Shin.

1995. Paper presented at 33rd Aerospace Sciences Meeting and Exhibit, 1995, Reno, United States.

Research output: Contribution to conferencePaper

TY - CONF

T1 - Numerical study on transonic blade-vortex interaction

T2 - Flowfield analysis

AU - Lin, San-Yih

AU - Chin, Yan Shin

PY - 1995/1/1

Y1 - 1995/1/1

N2 - Numerical investigations of aerodynamic sound generation due to transonic blade-vortex interaction were performed numerically. The numerical method is based on a third-order upwind finite volume scheme in space and a second-order explicit Runge-Kutta scheme in time. A standard transonic blade vortex interaction is presented to demonstrate two dominant sound waves, transonic and compressible waves. The fluctuation dilatation and correlation of the dilatation are presented to identify these two significant sound waves that travel upstream. Three unsteady shock wave motions, types A, B and C identified by Tijdeman, were simulated by changing the physical parameters, such as Mach number, vortex strength, and initial position of the vortex.

AB - Numerical investigations of aerodynamic sound generation due to transonic blade-vortex interaction were performed numerically. The numerical method is based on a third-order upwind finite volume scheme in space and a second-order explicit Runge-Kutta scheme in time. A standard transonic blade vortex interaction is presented to demonstrate two dominant sound waves, transonic and compressible waves. The fluctuation dilatation and correlation of the dilatation are presented to identify these two significant sound waves that travel upstream. Three unsteady shock wave motions, types A, B and C identified by Tijdeman, were simulated by changing the physical parameters, such as Mach number, vortex strength, and initial position of the vortex.

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M3 - Paper

ER -

Lin S-Y, Chin YS. Numerical study on transonic blade-vortex interaction: Flowfield analysis. 1995. Paper presented at 33rd Aerospace Sciences Meeting and Exhibit, 1995, Reno, United States.