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Title
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A Study of Aerodynamic Control in Stalled Flight Leading-Edge Vortex Formation Analysis
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Date
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1985
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Index Abstract
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Coming Soon
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Photo Quality
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Not Needed
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Report Number
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AFWAL TR 84-3090
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Creator
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Nathman, James K.
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Corporate Author
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Analytical Methods, Inc.
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Laboratory
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Flight Dynamics Laboratory
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Date Issued
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1985-02-01
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Extent
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61
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Identifier
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ADA153758
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Access Rights
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Approved for public release; distribution unlimited.
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Distribution Classification
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1
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Contract
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F33615-81-C-3626
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DoD Project
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2307
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DTIC Record Exists
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No
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Distribution Change Authority Correspondence
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None
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Abstract
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This report describes the theory and application of VORSEP, a wake preprocessor for panel methods that use an iterative procedure to determine the position of strongly interacting vortex sheets. The estimation of the wake geometry is based on slender body theory with separation. An unsteady, two-dimensional airfoil program was automated with the addition of routines to interpolate cross-sectional geometry from arbitrary three-dimensional bodies, generate multi-core wakes and synthesize a three-dimensional wake structure. Leading-edge wakes for a delta, straked wing and double delta are constructed and used in VSAERO, a three-dimensional panel method. The wake structures compare reasonably well to experimentally observed vortex core positions, while calculated pressures on the wings with the estimated wakes compare well near the nose but less well near the trailing edge. Keywords include: Panel methods; and Unsteady cross-flow analogy.
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Report Availability
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Full text available by request
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Provenance
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AFRL/VACA
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Type
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report
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Format
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61 pages ; 28 cm.