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Design and Experimental Results for a Natural-Laminar-Flow Airfoil for General Aviation ApplicationsA natural-laminar-flow airfoil for general aviation applications, the NLF(1)-0416, was designed and analyzed theoretically and verified experimentally in the Langley Low-Turbulence Pressure Tunnel. The basic objective of combining the high maximum lift of the NASA low-speed airfoils with the low cruise drag of the NACA 6-series airfoils was achieved. The safety requirement that the maximum lift coefficient not be significantly affected with transition fixed near the leading edge was also met. Comparisons of the theoretical and experimental results show excellent agreement. Comparisons with other airfoils, both laminar flow and turbulent flow, confirm the achievement of the basic objective.
Document ID
19810015487
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Somers, D. M. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
June 1, 1981
Subject Category
Aerodynamics
Report/Patent Number
NASA-TP-1861
L-14117
Accession Number
81N24022
Funding Number(s)
PROJECT: RTOP 505-31-33-05
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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