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Full-scale high angle-of-attack tests of an F/A-18This paper presents an overview of high angle-of-attack tests of a full-scale F/A-18 in the 80- by 120-Foot Wind Tunnel of the National Full-Scale Aerodynamic Complex at NASA Ames Research Center at Moffett Field, California. A production aircraft was tested over an angle-of-attack range of 18 to 50 deg and at wind speeds of up to 100 knots. These tests had three primary test objectives. Pneumatic and mechanical forebody flow control devices were tested at full-scale and shown to produce significant yawing moments for lateral control of the aircraft at high angles of attack. Mass flow requirements for the pneumatic system were found to scale with freestream density and speed rather than freestream dynamic pressure. Detailed measurements of the pressures buffeting the vertical tail were made and spatial variations in the buffeting frequency were found. The LEX fence was found to have a significant effect on the frequency distribution on the outboard surface of the vertical fin. In addition to the above measurements, an extensive set of data was acquired for the validation of computational fluid dynamics codes and for comparison with flight test and small-scale wind tunnel test results.
Document ID
19920062960
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Meyn, Larry A.
(NASA Ames Research Center Moffett Field, CA, United States)
Lanser, Wendy R.
(NASA Ames Research Center Moffett Field, CA, United States)
James, Kevin D.
(Sterling Federal Systems, Inc. Palo Alto, CA, United States)
Date Acquired
August 15, 2013
Publication Date
June 1, 1992
Subject Category
Aerodynamics
Report/Patent Number
AIAA PAPER 92-2676
Accession Number
92A45584
Distribution Limits
Public
Copyright
Other

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