Numerical study on transonic blade-vortex interaction: Flowfield analysis

San Yih Lin, Yan Shin Chin

Research output: Contribution to conferencePaperpeer-review

1 Citation (Scopus)


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
Event33rd Aerospace Sciences Meeting and Exhibit, 1995 - Reno, United States
Duration: 1995 Jan 91995 Jan 12


Other33rd Aerospace Sciences Meeting and Exhibit, 1995
Country/TerritoryUnited States

All Science Journal Classification (ASJC) codes

  • Space and Planetary Science
  • Aerospace Engineering


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