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Prediction of unsteady loads on maneuvering delta wings using time-accurate Euler schemesThree-dimensional steady and unsteady vortex-dominated flows around sharp-edged delta wings are considered in this paper. The problem is formulated by using the unsteady conservative Euler equations for the flow relative motion with respect to a moving frame of reference. An implicit approximately-factored finite volume scheme is used to solve the resulting equations on a three-dimensional computational grid which is generated by using a modified Joukowski transformation in cross-flow planes at the grid chord stations. The scheme is applied to a delta wing undergoing pitching oscillation around a large angle of attack. The initial conditions correspond to a steady flow around a delta wing of aspect ratio of one, freestream Mach number of 0.3 and mean angle of attack of 20.5. The steady flow results are compared with those of an explicit computational scheme and the experimental data, and they are in good agreement.
Document ID
19880045007
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Kandil, Osama A.
(Old Dominion Univ. Norfolk, VA, United States)
Chuang, H. Andrew
(Old Dominion University Norfolk, VA, United States)
Date Acquired
August 13, 2013
Publication Date
January 1, 1988
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 88-2280
Meeting Information
Meeting: Structures, Structural Dynamics and Materials Conference
Location: Williamsburg, VA
Country: United States
Start Date: April 18, 1988
End Date: April 20, 1988
Sponsors: Structures
Accession Number
88A32234
Funding Number(s)
CONTRACT_GRANT: NAG1-648
Distribution Limits
Public
Copyright
Other

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