Numerical study on reduction of transonic blade-vortex interaction noise

San-Yih Lin, Yan Shin Chin, Bae Yih Hwang

Research output: Contribution to journalArticle

1 Citation (Scopus)

Abstract

Reduction of noise caused by transonic blade-vortex interaction (BVI) is investigated numerically. The near and midfield flowfields are obtained by an Euler solver. The Euler solver is based on a third-order upwind finite volume scheme in space and a second-order explicit Runge-Kutta scheme in time. Far-field noise is then obtained from the Kirchhoff method. Two control techniques, blowing/suction and porous wall on the airfoil surface, are investigated to reduce two dominant disturbances, transonic and compressibility waves, in the BVI noise signature. Numerical results indicate that the blowing/suction control technique reduces the fluctuations generated by the transonic wave but has little influence on the compressibility wave unless it is employed at the leading edge of the blade. With surface porosity control both compressibility and transonic waves are satisfactorily reduced.

Original languageEnglish
Pages (from-to)796-802
Number of pages7
JournalJournal of Aircraft
Volume37
Issue number5
DOIs
Publication statusPublished - 2000 Jan 1

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Vortex flow
Compressibility
Blow molding
Airfoils
Porosity

All Science Journal Classification (ASJC) codes

  • Aerospace Engineering

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Lin, San-Yih ; Chin, Yan Shin ; Hwang, Bae Yih. / Numerical study on reduction of transonic blade-vortex interaction noise. In: Journal of Aircraft. 2000 ; Vol. 37, No. 5. pp. 796-802.
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Numerical study on reduction of transonic blade-vortex interaction noise. / Lin, San-Yih; Chin, Yan Shin; Hwang, Bae Yih.

In: Journal of Aircraft, Vol. 37, No. 5, 01.01.2000, p. 796-802.

Research output: Contribution to journalArticle

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