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Supercritical maneuvering fighter configuration. Wind-tunnel investigation at Mach numbers of 0.60 to 0.95A wind tunnel investigation was conducted to study the application of supercritical technology to highly maneuverable combat aircraft. The configuration studied has a leading-edge sweep of 45 deg and an aspect ratio of 3.28. Two supercritical-wing shapes were tested at Mach numbers from 0.60 to 0.95 with angles of attack from -2 deg to 17 deg. On supercritical wing was designed to achieve a high level of transonic maneuver performance at a Mach number of 0.90; however, excessive flow separation developed on this wing at a Mach number of 0.85. A second supercritical wing was tested which had significantly reduced flow separation and improved drag characteristics at a Mach number of 0.85 and maintained the performance of the original wing at the higher Mach numbers. Leading-edge vortex generators did not improve the performance of the second wing; however, a sharp leading-edge flap produced sizable drag reductions at Mach numbers from 0.60 to 0.90.
Document ID
19820023427
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Mann, M. J. (NASA Langley Research Center Hampton, VA, United States)
Mercer, C. E. (NASA Langley Research Center Hampton, VA, United States)
Campbell, R. L. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
September 1, 1982
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-84513
L-15399
NAS 1.15:84513
Accession Number
82N31303
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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