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Experimental Results for a Flapped Natural-laminar-flow Airfoil with High Lift/drag RatioExperimental results have been obtained for a flapped natural-laminar-flow airfoil, NLF(1)-0414F, in the Langley Low-Turbulence Pressure Tunnel. The tests were conducted over a Mach number range from 0.05 to 0.40 and a chord Reynolds number range from about 3.0 x 10(6) to 22.0 x 10(6). The airfoil was designed for 0.70 chord laminar flow on both surfaces at a lift coefficient of 0.40, a Reynolds number of 10.0 x 10(6), and a Mach number of 0.40. A 0.125 chord simple flap was incorporated in the design to increase the low-drag, lift-coefficient range. Results were also obtained for a 0.20 chord split-flap deflected 60 deg.
Document ID
19860016814
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Mcghee, R. J. (NASA Langley Research Center Hampton, VA, United States)
Viken, J. K. (Mandex, Inc. Falls Church, Va., United States)
Pfenninger, W. (Engineering Science Consultants Grafton, Va., United States)
Beasley, W. D. (NASA Langley Research Center Hampton, VA, United States)
Harvey, W. D. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
May 1, 1984
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-85788
NAS 1.15:85788
Accession Number
86N26286
Funding Number(s)
PROJECT: RTOP 505-31-23-06
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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