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Low-speed aerodynamic characteristics of a 17-percent-thick medium speed airfoil designed for general aviation applicationsWind tunnel tests were conducted to determine the low speed two dimensional aerodynamic characteristics of a 17 percent thick medium speed airfoil (MS(1)-0317) designed for general aviation applications. The results were compared with data for the 17 percent thick low speed airfoil (LS(1)-0417) and the 13 percent thick medium speed airfoil (MS(1)-0313). Theoretical predictions of the drag rise characteristics of this airfoil are also provided. The tests were conducted in the Langley low turbulence pressure tunnel over a Mach number range from 0.10 to 0.32, a chord Reynolds number range from 2 million to 12 million, and an angle of attack range from about -8 to 20 deg.
Document ID
19830008019
Acquisition Source
Legacy CDMS
Document Type
Technical Publication (TP)
Authors
Mcghee, R. J.
(NASA Langley Research Center Hampton, VA, United States)
Beaseley, W. D.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 4, 2013
Publication Date
December 1, 1980
Subject Category
Aerodynamics
Report/Patent Number
NASA-TP-1786
NAS 1.60:1786
L-13900
Report Number: NASA-TP-1786
Report Number: NAS 1.60:1786
Report Number: L-13900
Accession Number
83N16290
Funding Number(s)
PROJECT: RTOP 505-31-33-05
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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