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The NASA Langley laminar-flow-control experiment on a swept, supercritical airfoil: Evaluation of initial perforated configurationThe initial evaluation of a large-chord, swept, supercritical airfoil incorporating an active laminar-flow-control (LFC) suction system with a perforated upper surface is documented in a chronological manner, and the deficiencies in the suction capability of the perforated panels as designed are described. The experiment was conducted in the Langley 8-Foot Transonic Pressure Tunnel. Also included is an evaluation of the influence of the proximity of the tunnel liner to the upper surface of the airfoil pressure distribution.
Document ID
19920012953
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Harris, Charles D. (NASA Langley Research Center Hampton, VA, United States)
Brooks, Cuyler W., Jr. (NASA Langley Research Center Hampton, VA, United States)
Clukey, Patricia G. (NASA Langley Research Center Hampton, VA, United States)
Stack, John P. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 6, 2013
Publication Date
April 1, 1992
Subject Category
Aerodynamics
Report/Patent Number
L-16856
NAS 1.15:4309
NASA-TM-4309
Report Number: L-16856
Report Number: NAS 1.15:4309
Report Number: NASA-TM-4309
Accession Number
92N22196
Funding Number(s)
PROJECT: RTOP 505-61-21-03
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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