Aerodynamic characteristics of NACA 0012 airfoil section at angles of attack from 0 degrees to 180 degrees Page: 3 of 24
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NATIONAL ADVISORY COMMITTEE FOR AERONAUTICS
TECHNICAL NOTE 3361
AERODYNAMIC CHARACTERISTICS OF NACA 0012 AIRFOIL SECTION
AT ANGLES OF ATTACK FROM 00 TO 1800
By Chris C. Critzos, Harry H. Heyson,
and Robert W. Boswinkle, Jr.
SU4MARY
The aerodynamic characteristics of the NACA 0012 airfoil section
have been obtained at angles of attack from 00 to 1800. Data were
obtained at a Reynolds number of 1.8 x 106 with the airfoil surfaces
smooth and with roughness applie at the leading and trailing edges and
at a Reynolds number of 0.5 x 100 with the airfoil surfaces smooth. The
tests were conducted in the Langley low-turbulence pressure tunnel at
Mach numbers no greater than 0.15.
After the stall with the rounded edge of the airfoil foremost, a
second lift-coefficient peak was obtained at an angle of attack of about
4~o; initial and second lift-coefficient peaks were also obtained with
the sharp edge of the airfoil foremost. The application of roughness
and a reduction of the Reynolds number had only small effects on the lift
coefficients obtained at angles of attack between 250 and 1250. A discon-
tinuous variation of lift coefficient with angle of attack was obtained
near an angle of attack of 1800 at the lower test Reynolds number with
the airfoil surfaces smooth.
At a Reynolds number of 1.8 x 106, the drag coefficient at an angle
of attack of 1800 was about twice that for an angle of attack of 00.
The drag coefficiegts obtained at an angle of attack of 900 at a Reynolds
number of 1.8 x 10 were 2.08 and 2.02 with the airfoil surfaces in a
smooth and in a rough condition, respectively; the drag coefficient
obtained at an angle of attack of 900 and a Reynolds number of 0.5 x 106
with the airfoil surfaces smooth was 1.95. These values compare favorably
with the drag coefficient of about 2.0 obtained from the literature for
a flat plate of infinite aspect ratio inclined normal to the flow.
INTRODUCTION
A rotary-wing aircraft in forward flight encounters very high local
angles of attack at inboard locations of the retreating rotor blades.
The local angle of attack may be near 1800o where the local rotational
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Critzos, Chris C.; Heyson, Harry H. & Boswinkle, Robert W., Jr. Aerodynamic characteristics of NACA 0012 airfoil section at angles of attack from 0 degrees to 180 degrees, report, January 1955; (https://digital.library.unt.edu/ark:/67531/metadc56017/m1/3/: accessed April 24, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.