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Simulation of blunt-fin-induced shock wave and turbulent boundary-layer interactionA supersonic flow over a blunt fin mounted on a flat plate is numerically simulated. The fin shock causes the boundary layer to separate and results in a complicated, three-dimensional shockwave and boundary-layer interaction. The computed result is in good agreement with the measured pressure on the fin and the flat plate. The main features, such as peak pressure on the fin leading edge and a double peak pressure on the plate, are closely predicted. The role of the horseshoe vortex is discussed. The vortex leads to the development of high-speed flow, and, hence, low-pressure regions on the fin and the plate. Different thicknesses of the incoming boundary layer have been studied. Varying the thicknesses by an order of magnitude shows that the size of the horseshoe vortex and therefore the spatial extent of the interaction are inviscid-dominated, and are weakly dependent on the Reynolds number. Colored graphics are used to show details of the interaction flow field.
Document ID
19840038514
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Hung, C.-M.
(NASA Ames Research Center Moffett Field, CA, United States)
Buning, P. G.
(NASA Ames Research Center Moffett Field, CA, United States)
Date Acquired
August 12, 2013
Publication Date
January 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 84-0457
Accession Number
84A21301
Distribution Limits
Public
Copyright
Other

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