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An Analytical Design Procedure for the Determination of Effective Leading Edge Extensions on Thick Delta WingsAn analytical design procedure for leading edge extensions (LEE) was developed for thick delta wings. This LEE device is designed to be mounted to a wing along the pseudo-stagnation stream surface associated with the attached flow design lift coefficient of greater than zero. The intended purpose of this device is to improve the aerodynamic performance of high subsonic and low supersonic aircraft at incidences above that of attached flow design lift coefficient, by using a vortex system emanating along the leading edges of the device. The low pressure associated with these vortices would act on the LEE upper surface and the forward facing area at the wing leading edges, providing an additional lift and effective leading edge thrust recovery. The first application of this technique was to a thick, round edged, twisted and cambered wing of approximately triangular planform having a sweep of 58 deg and aspect ratio of 2.30. The panel aerodynamics and vortex lattice method with suction analogy computer codes were employed to determine the pseudo-stagnation stream surface and an optimized LEE planform shape.
Document ID
19840011216
Acquisition Source
Langley Research Center
Document Type
Contractor Report (CR)
Authors
Farhad Ghaffari (Old Dominion University Norfolk, Virginia, United States)
Sushil K Chaturvedi (Old Dominion University Norfolk, Virginia, United States)
Date Acquired
September 4, 2013
Publication Date
May 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.26:172351
NASA-CR-172351
Accession Number
84N19284
Funding Number(s)
CONTRACT_GRANT: NAS1-17099
Distribution Limits
Public
Copyright
Use by or on behalf of the US Gov. Permitted.

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