Effects of independent variations of mach number and reynolds number on the maximum lift coefficients of four NACA 6-series airfoil sections Page: 3 of 33
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NACA TN 2824
In predicting the low-speed performance characteristics of aircraft
with stalling speeds corresponding to Mach numbers of about 0.1, the
maximum lift coefficient has been considered to be free of compressibility
effects. High-speed performance requirements, however; have resulted in
stalling speeds corresponding to Mach numbers of 0.2 or higher where the
effects of compressibility may be significant. Inasmuch as the stalling
speed is indicative of the landing speed and of the speeds involved in_
low-speed maneuvers, a knowledge of the effects of Mach number and
Reynolds number on maximum lift is desirable. A series of investigations
have been conducted by the National Advisory Committee for Aeronautics
to study the effects of Mach number and Reynolds number on maximum lift
coefficient (see refs. 1 to 8). In most of these investigations, the
results were obtained from tests of three-dimensional models and the Mach
number varied simultaneously with the Reynolds number. Investigations of
two-dimensional models in which the Mach number is varied while the
Reynolds number is held constant are needed to obtain an indication of
the magnitude of the effects on two-dimensional sections.
An investigation has therefore been made in the Langley low-turbulence
pressure tunnel of four airfoil sections ranging in thickness from 6 to
15 percent chord to determine the effects of Mach number when varied
independently of the Reynolds number on the maximum lift coefficient for
several constant values of the Reynolds number. The results of this
investigation are presented in this paper.
The investigation consisted of -measurements of the section lift
characteristics from about zero lift to beyond the stall for the
NACA 65-006, 64-009, 64-210, and 642-215 airfoil sections. The range
of Mach number extended from 0.1 to approximately 0.5; whereas, the range
of Reynolds number extended from 1.5 x 106 to 9.0 x 106. Data were obtained
for the airfoil sections with aerodynamically smooth surfaces and with
c Z section lift coefficient, Z/qc
c Zmax maximum section lift coefficient
maximum wing lift coefficient
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Racisz, Stanley F. Effects of independent variations of mach number and reynolds number on the maximum lift coefficients of four NACA 6-series airfoil sections, report, November 1, 1952; (digital.library.unt.edu/ark:/67531/metadc56326/m1/3/: accessed December 14, 2017), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.