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A parametric study of three-dimensional separation at a wing/body junction for supersonic free-stream conditionsThe problem of three-dimensional separation at a wing/body junction has been investigated numerically using a three-dimensional Navier-Stokes code which employs the MacCormack's time split finite volume technique. An algebraic grid generation technique is used for generating the grid at a wing/body junction. Specific computational results on velocity and pressure distribution in the separated flow region are compared with the experimental results. A parametric study of flow parameters such as Mach number and Reynolds number have been carried out to understand their effect in interaction flow field. The parametric study indicates a strong dependency of the number of vortices at the junction on Mach number and Reynolds number.
Document ID
19890060286
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Lakshmanan, B.
(Old Dominion Univ. Norfolk, VA, United States)
Tiwari, S. N.
(Old Dominion University Norfolk, VA, United States)
Hussaini, M. Y.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
August 14, 2013
Publication Date
January 1, 1989
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 89-2198
Meeting Information
Meeting: AIAA Applied Aerodynamics Conference
Location: Seattle, WA
Country: United States
Start Date: July 31, 1989
End Date: August 2, 1989
Sponsors: AIAA
Accession Number
89A47657
Funding Number(s)
CONTRACT_GRANT: NAG1-530
Distribution Limits
Public
Copyright
Other

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