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Low-speed wind-tunnel results for symmetrical NASA LS(1)-0013 airfoilA wind-tunnel test has been conducted in the Langley Low-Turbulence Pressure Tunnel to evaluate the performance of a symmetrical NASA LS(1)-0013 airfoil which is a 13-percent-thick, low-speed airfoil. The airfoil contour was obtained from the thickness distribution of a 13-percent-thick, high-performance airfoil developed for general aviation airplanes. The tests were conducted at Mach numbers from 0.10 tp 0.37 over a Reynolds number range from about 0.6 to 12.0 X 10 to the 6th power. The angle of attack varied from about -8 to 20 degrees. The results indicate that the aerodynamic characteristics of the present airfoil are similar to, but slightly better than, those of the NACA 0012 airfoil.
Document ID
19870016600
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Ferris, James C. (NASA Langley Research Center Hampton, VA, United States)
Mcghee, Robert J. (NASA Langley Research Center Hampton, VA, United States)
Barnwell, Richard W. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 5, 2013
Publication Date
August 1, 1987
Subject Category
Aerodynamics
Report/Patent Number
L-16279
NASA-TM-4003
NAS 1.15:4003
Accession Number
87N26033
Funding Number(s)
PROJECT: RTOP 505-60-21-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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