The results of wind-tunnel tests to a Mach number of 0.90 of a four-engine, propeller-driven airplane configuration having a wing with 40 degrees of sweepback and an aspect ratio of 10 Page: 4 of 172
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NACA TN 3789
c local wing chord parallel to the plane of symmetry
c' local wing chord normal to the reference sweep line (see table I)
b/2
b/ c'dy
c wing mean aerodynamic chord,
J c ay
CZi ving-section design lift coefficient
D propeller diameter
h maximum thickness of propeller-blade section
hp horsepower
it incidence of the horizontal tail with respect to the wing-root chord
3 propeller advance ratio,
Zt tail length, distance between the quarter points of the mean aero-
dynamic chords of the wing and the horizontal tail, measured
parallel to the plane of symmetry
M free-stream Mach number
n propeller rotational speed.
P shaft power per motor
pv2
q free-stream dynamic pressure, -
R Reynolds number, based on wing mean aerodynamic chord
R' propeller-tip radius
r propeller-blade-section radius
S area of the semispan wing, flaps off
T thrust per propeller, parallel to stream
Tc thrust coefficient per propeller,
t wing-section thickness
V free-stream velocity
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Edwards, George G.; Dickson, Jerald K.; Sutton, Fred B. & Demele, Fred A. The results of wind-tunnel tests to a Mach number of 0.90 of a four-engine, propeller-driven airplane configuration having a wing with 40 degrees of sweepback and an aspect ratio of 10, report, September 1956; (https://digital.library.unt.edu/ark:/67531/metadc56062/m1/4/: accessed April 22, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.