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Natural Laminar Flow Flight ExperimentA supercritical airfoil section was designed with favorable pressure gradients on both the upper and lower surfaces. Wind tunnel tests were conducted in the Langley 8 Foot Transonic Pressure Tunnel. The outer wing panels of the F-111 TACT airplane were modified to incorporate partial span test gloves having the natural laminar, flow profile. Instrumentation was installed to provide surface pressure data as well as to determine transition location and boundary layer characteristics. The flight experiment encompassed 19 flights conducted with and without transition fixed at several locations for wing leading edge sweep angles which varied from 10 to 26 at Mach numbers from 0.80 to 0.85 and altitudes of 7620 meters and 9144 meters. Preliminary results indicate that a large portion of the test chord experienced laminar flow.
Document ID
19810010484
Acquisition Source
Legacy CDMS
Document Type
Conference Paper
Authors
Steers, L. L. (NASA Hugh L. Dryden Flight Research Center Edwards, CA, United States)
Date Acquired
August 11, 2013
Publication Date
February 1, 1981
Publication Information
Publication: NASA. Langley Research Center Advan. Aerodyn. and Active Controls
Subject Category
Aerodynamics
Accession Number
81N19010
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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IDRelationTitle19810010475Collected WorksAdvanced aerodynamics and active controls. Selected NASA research
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