Three-dimensional supersonic vortex breakdownThree-dimensional supersonic vortex-breakdown problems in bound and unbound domains are solved. The solutions are obtained using the time-accurate integration of the unsteady, compressible, full Navier-Stokes (NS) equations. The computational scheme is an implicit, upwind, flux-difference splitting, finite-volume scheme. Two vortex-breakdown applications are considered in the present paper. The first is for a supersonic swirling jet which is issued from a nozzle into a supersonic uniform flow at a lower Mach number than that of the swirling jet. The second is for a supersonic swirling flow in a configured circular duct. In the first application, an extensive study of the effects of grid fineness, shape and grid-point distribution on the vortex breakdown is presented. Four grids are used in this study and they show a substantial dependence of the breakdown bubble and shock wave on the grid used. In the second application, the bubble-type and helix-type vortex breakdown have been captured.
Kandil, Osama A. (NASA Langley Research Center Hampton, VA, United States)
Kandil, Hamdy A. (Old Dominion Univ. Norfolk, VA, United States)
Liu, C. H. (NASA Langley Research Center Hampton, VA, United States)
August 16, 2013
January 1, 1993
AIAA PAPER 93-0526
Meeting: AIAA, Aerospace Sciences Meeting and Exhibit