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A computer program for estimating the aerodynamic characteristics of NACA 16-series airfoilsA computer program written in a table ""look-up'' format, is presented which provides a comprehensive data base on NACA 16-series airfoils. The geometry covered is limited to cambers for a design-lift coefficient from 0.0 to 0.7 and thickness ratios from 4 to 21%. The data include Mach numbers from 0.3 to 1.6, angles of attack from -4 to 8 degrees, and lift coefficients from 0.0 to 0.8. Extrapolation is used to obtain data from Mach numbers, angles of attack, and lift coefficients beyond those for which data are available. A routine to adjust the lift and drag coefficients beyond stall is included. The uses and limitations of the program are also discussed.
Document ID
19840003077
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Maksymiuk, C. M.
(NASA Langley Research Center Hampton, VA, United States)
Watson, S. A.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
September 1, 1983
Subject Category
Aerodynamics
Report/Patent Number
NASA-TM-85696
NAS 1.15:85696
Accession Number
84N11145
Funding Number(s)
PROJECT: RTOP 505-43-43-01
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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