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.
Format:	Report
Sprache:	eng
Schlagworte:	Aerodynamics
Online-Zugang:	Volltext bestellen
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