Numerical investigations of aerodynamic sound generation due to transonic blade-vortex interaction were performed numerically. The numerical method is basedon a third-order upwind finite-volume scheme in space and a second-order explicit Runge—Kutta scheme in tune. A standard transonic blade-vortex interaction is presented to demonstrate two dominant sound waves, transonic and compressibility waves. The fluctuation dilatation is presented to identify these two significant sound waves which travel upstream. Three unsteady shock wave motions, types A, B, and C identified by Tijdeman and Seebass, were simulated by changing the physical parameters, such as Mach number, vortex strength, and initial position of the vortex.
All Science Journal Classification (ASJC) codes
- Aerospace Engineering