Experimental Results for a Flapped Natural-laminar-flow Airfoil with High Lift/drag Ratio

Experimental 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 w...

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Hauptverfasser:	Mcghee, R. J., Viken, J. K., Pfenninger, W., Beasley, W. D., Harvey, W. D.
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Sprache:	eng
Schlagworte:	Aerodynamics
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creator	Mcghee, R. J. Viken, J. K. Pfenninger, W. Beasley, W. D. Harvey, W. D.
description	Experimental 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.
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D.</creatorcontrib><description>Experimental 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. 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D.</creatorcontrib><title>Experimental Results for a Flapped Natural-laminar-flow Airfoil with High Lift/drag Ratio</title><description>Experimental 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. 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D.</author></sort><facets><frbrtype>5</frbrtype><frbrgroupid>cdi_FETCH-nasa_ntrs_198600168143</frbrgroupid><rsrctype>reports</rsrctype><prefilter>reports</prefilter><language>eng</language><creationdate>1984</creationdate><topic>Aerodynamics</topic><toplevel>online_resources</toplevel><creatorcontrib>Mcghee, R. J.</creatorcontrib><creatorcontrib>Viken, J. K.</creatorcontrib><creatorcontrib>Pfenninger, W.</creatorcontrib><creatorcontrib>Beasley, W. D.</creatorcontrib><creatorcontrib>Harvey, W. D.</creatorcontrib><collection>NASA Scientific and Technical Information</collection><collection>NASA Technical Reports Server</collection></facets><delivery><delcategory>Remote Search Resource</delcategory><fulltext>fulltext_linktorsrc</fulltext></delivery><addata><au>Mcghee, R. J.</au><au>Viken, J. K.</au><au>Pfenninger, W.</au><au>Beasley, W. D.</au><au>Harvey, W. D.</au><format>book</format><genre>unknown</genre><ristype>RPRT</ristype><btitle>Experimental Results for a Flapped Natural-laminar-flow Airfoil with High Lift/drag Ratio</btitle><date>1984-05-01</date><risdate>1984</risdate><abstract>Experimental 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.</abstract><cop>Legacy CDMS</cop><oa>free_for_read</oa></addata></record>
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title	Experimental Results for a Flapped Natural-laminar-flow Airfoil with High Lift/drag Ratio
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