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Design and experimental results for a flapped natural-laminar-flow airfoil for general aviation applications

Author: Dan M Somers; United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
Publisher: Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va.] : [For sale by the National Technical Information Service], 1981.
Series: NASA technical paper, 1865.
Edition/Format:   Print book : National government publication : EnglishView all editions and formats
Summary:
A flapped natural laminar flow airfoil for general aviation applications, the NLF(1)-0215F, has been 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 has been achieved. The safety requirement that the maximum lift  Read more...
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Additional Physical Format: Online version:
Somers, Dan M.
Design and experimental results for a flapped natural-laminar-flow airfoil for general aviation applications.
Washington, D.C. : National Aeronautics and Space Administration, Scientific and Technical Information Branch ; [Springfield, Va. : For sale by the National Technical Information Service], 1981
(OCoLC)761450205
Material Type: Government publication, National government publication, Internet resource
Document Type: Book, Internet Resource
All Authors / Contributors: Dan M Somers; United States. National Aeronautics and Space Administration. Scientific and Technical Information Branch.
OCLC Number: 10584076
Notes: Distributed to depository libraries in microfiche.
"June 1981"--Cover.
Subject category 02.
Description: 122 pages : illustrations ; 28 cm.
Series Title: NASA technical paper, 1865.
Responsibility: Dan M. Somers.

Abstract:

A flapped natural laminar flow airfoil for general aviation applications, the NLF(1)-0215F, has been 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 has been achieved. The safety requirement that the maximum lift coefficient not be significantly affected with transition fixed near the leading edge has also been met. Comparisons of the theoretical and experimental results show generally good agreement.

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