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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.
Document ID
19930039270
Document Type
Conference Paper
Authors
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)
Date Acquired
August 16, 2013
Publication Date
January 1, 1993
Subject Category
AERODYNAMICS
Report/Patent Number
AIAA PAPER 93-0526
Meeting Information
AIAA, Aerospace Sciences Meeting and Exhibit(Reno, NV)
Funding Number(s)
CONTRACT_GRANT: NAG1-994
Distribution Limits
Public
Copyright
Other