A Study of Aerodynamic Control in Stalled Flight Leading-Edge Vortex Formation Analysis

Item

Title
A Study of Aerodynamic Control in Stalled Flight Leading-Edge Vortex Formation Analysis
Date
1985
Index Abstract
Coming Soon
Photo Quality
Not Needed
Report Number
AFWAL TR 84-3090
Creator
Nathman, James K.
Corporate Author
Analytical Methods, Inc.
Laboratory
Flight Dynamics Laboratory
Date Issued
1985-02-01
Extent
61
Identifier
ADA153758
Access Rights
Approved for public release; distribution unlimited.
Distribution Classification
1
Contract
F33615-81-C-3626
DoD Project
2307
DTIC Record Exists
No
Distribution Change Authority Correspondence
None
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.
Report Availability
Full text available by request
Provenance
AFRL/VACA
Type
report
Format
61 pages ; 28 cm.