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Aerodynamic characteristics of the 10-percent-thick NASA supercritical airfoil 33 designed for a normal-force coefficient of 0.7A 10-percent-thick supercritical airfoil based on an off-design sonic-pressure plateau criterion was developed and experimental aerodynamic characteristics measured. The airfoil had a design normal-force coefficient of 0.7 and was identified as supercritical airfoil 33. Results show the airfoil to have good drag rise characteristics over a wide range of normal-force coefficients with no measurable shock losses up to the Mach numbers at which drag divergence occurred for normal-force coefficients up to 0.7. Comparisons of experimental and theoretical characteristics were made and composite drag rise characteristics were derived for normal-force coefficients of 0.5 and 0.7 and a Reynolds number of 40 million.
Document ID
19830002805
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Harris, C. D. (NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
January 1, 1975
Subject Category
Aerodynamics
Report/Patent Number
NAS 1.15:X-72711
NASA-TM-X-72711
Accession Number
83N11075
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.

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