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Full-scale wind-tunnel tests of high-lift system modifications on a carrier based fighter aircraftModifications to the high-lift system of a full-scale F/A-I8A were tested in the 80- by 120-Foot Wind Tunnel of the National Full-Scale Aerodynamics Complex at the NASA Ames Research Center in Moffett Field, California. The objective was to measure the effect of simple modifications on the aerodynamic performance of the high-lift system. The modifications included the placement of a straight fairing in the shroud cove above the trailing-edge flap and the addition of seals to prevent air leakage through the hinge lines of the leading-edge flap, the trailing-edge shroud, and the wing fold. The test was carried out on an actual F/A-18A with it's flaps deployed in the landing approach configuration. The angle of attack ranged from 0 to 16 degrees and the wind speed was 100 knots. At an angle of attack of 8 degrees, the trimmed lift coefficient was improved by 0.09 with all wing seals in place. This corresponds to a reduction in the approach speed for the F/A-I8A of about 5 knots. The seal along the wing fold hinge, a feature present on many naval aircraft, provided one third of the total increment in trimmed lift. A comparison of the full-scale wind-tunnel results with those obtained from flight test is also presented.
Document ID
Document Type
Conference Paper
Meyn, Larry A.
(NASA Ames Research Center Moffett Field, CA, United States)
Zell, Peter T.
(NASA Ames Research Center Moffett Field, CA, United States)
Hagan, John L.
(NASA Ames Research Center Moffett Field, CA, United States)
Schoch, David
(McDonnell Douglas Corp. Saint Louis, MO, United States)
Date Acquired
August 16, 2013
Publication Date
February 1, 1993
Subject Category
Research And Support Facilities (Air)
Report/Patent Number
AIAA PAPER 93-1015
Meeting Information
AIAA, AHS, and ASEE, Aerospace Design Conference(Irvine, CA)
Accession Number
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