A Study of Aerodynamic Control in Stalled Flight Leading-Edge Vortex Formation Analysis
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Report Number: AFWAL TR 84-3090
Author(s): Nathman, James K.
Corporate Author(s): Analytical Methods, Inc.
Laboratory: Flight Dynamics Laboratory
Date of Publication: 1985-02-01
Pages: 61
Contract: F33615-81-C-3626
DoD Project: 2307
DoD Task:
Identifier: ADA153758
Abstract:
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.
Provenance: AFRL/VACA
Author(s): Nathman, James K.
Corporate Author(s): Analytical Methods, Inc.
Laboratory: Flight Dynamics Laboratory
Date of Publication: 1985-02-01
Pages: 61
Contract: F33615-81-C-3626
DoD Project: 2307
DoD Task:
Identifier: ADA153758
Abstract:
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.
Provenance: AFRL/VACA