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Airfoil modification effects on subsonic and transonic pressure distributions and performance for the EA-6B airplaneLongitudinal characteristics and wing-section pressure distributions are compared for the EA-6B airplane with and without airfoil modifications. The airfoil modifications were designed to increase low-speed maximum lift for maneuvering, while having a minimal effect on transonic performance. Section contour changes were confined to the leading-edge slat and trailing-edge flap regions of the wing. Experimental data are analyzed from tests in the Langley 16-Foot Transonic Tunnel on the baseline and two modified wing-fuselage configurations with the slats and flaps in their retracted positions. Wing modification effects on subsonic and transonic performance are seen in wing-section pressure distributions of the various configurations at similar lift coefficients. The modified-wing configurations produced maximum lift coefficients which exceeded those of the baseline configuration at low-speed Mach numbers (0.300 and 0.400). This benefit was related to the behavior of the wing upper surface leading-edge suction peak and the behavior of the trailing-edge pressure. At transonic Mach numbers (0.725 to 0.900), the wing modifications produced a somewhat stronger nose-down pitching moment, a slightly higher drag at low-lift levels, and a lower drag at higher lift levels.
Document ID
19950019962
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Allison, Dennis O. (NASA Langley Research Center Hampton, VA, United States)
Sewall, William G. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
May 1, 1995
Subject Category
Aerodynamics
Report/Patent Number
L-17360
NASA-TP-3516
NAS 1.60:3516
Accession Number
95N26382
Funding Number(s)
PROJECT: RTOP 505-59-10-30
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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