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Low speed aerodynamic characteristics of NACA 6716 and NACA 4416 airfoils with 35 percent-chord single-slotted flapsAn investigation was conducted in a low-turbulence pressure tunnel to determine the two-dimensional lift and pitching-moment characteristics of an NACA 6716 and an NACA 4416 airfoil with 35-percent-chord single-slotted flaps. Both models were tested with flaps deflected from 0 deg to 45 deg, at angles of attack from minus 6 deg to several degrees past stall, at Reynolds numbers from 3.0 million to 13.8 million, and primarily at a Mach number of 0.23. Tests were also made to determine the effect of several slot entry shapes on performance.
Document ID
19740013521
Acquisition Source
Legacy CDMS
Document Type
Technical Memorandum (TM)
Authors
Bingham, G. J.
(NASA Langley Research Center Hampton, VA, United States)
Noonan, K. W.
(NASA Langley Research Center Hampton, VA, United States)
Date Acquired
September 3, 2013
Publication Date
May 1, 1974
Subject Category
Aerodynamics
Report/Patent Number
L-8410
NASA-TM-X-2623
Report Number: L-8410
Report Number: NASA-TM-X-2623
Accession Number
74N21634
Funding Number(s)
PROJECT: RTOP 760-17-01-10
Distribution Limits
Public
Copyright
Work of the US Gov. Public Use Permitted.
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