Scale-effect tests in a turbulent tunnel of the NACA 65(sub 3)-418, a = 1.0 airfoil section with 0.20-airfoil-chord split flap Page: 3 of 22
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NACA ACR No. 14122
NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS
ADVA1 CE CONFIDENTIAL REPORT- .-
SCALE-EFFECT TESTS IN A TURBULENT TUNNEL OF
THE NACA 655-418, a = 1.0 AIRFOIL SECTION
WITH 0.20-ATRFOIL-CHORD SPLIT FLAP
By Warren A. Tucker and Arthur R. Wallace
The effect of Reynolds number on the aerodynamic
characteristics of a low-drag airfoil section tested
under conditions of relatively high stream turbulence
was determined by tests in the LMAL 7- by 10-foot tunnel
of the NACA 653-18S, a = 1.0 airfoil section with a
split flap having a chord 20 percent of the airfoil
chord. Tge Reynolds number ranged from 0.19 to
2.99 x 10 ; the Mach number attained was never greater
than 0.10. The data are presented as curves of section
angle of attack, section profile-drag coefficient, and
section pitching-moment coefficient against section
lift coefficient for various flap deflections.
The maximum lift coefficient increased with Reynolds
number. Deflecting the flap added an increment of
maximum lift coefficient that seemed to be almost con-
stant at all Reynolds numbers. The slope of the section
lift curve with flap deflected showed no consistent
variation with Reynolds number, although the slope of
the section lift curve for the plain airfoil increased
up to a Reynolds number of about 1.0 x 106 and then
remained nearly constant up to a Reynolds number of
about 3.0 x 10 , the limit of the tests. For flap
deflections above 150, the slope of the section lift
curve decreased with increase in flap deflection.
The section drag coefficient with flap deflected
remained almost constant with Reynolads number, although
the section drag coefficient for the plain airfoil
decreased up to a Reynolds number of about o.8 x 106
and then remained nearly constant to a Reynolds number
of about 3.0 x 10 .
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Tucker, Warren A. & Wallace, Arthur R. Scale-effect tests in a turbulent tunnel of the NACA 65(sub 3)-418, a = 1.0 airfoil section with 0.20-airfoil-chord split flap, report, September 1944; (digital.library.unt.edu/ark:/67531/metadc61404/m1/3/: accessed January 20, 2019), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.