Analysis 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: 6 of 171
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NACA TN 3790
R' propeller-tip radius
r propeller-blade-section radius
S area of the semispan wing, flaps off
St area of semispan tail
T thrust per propeller, parallel to free stream
Tc thrust coefficient per propeller, ,T
t wing-section maximum thickness
V free-stream velocity
V tail volume, -S
W weight of assumed full-scale airplane
X longitudinal force, parallel to stream and positive in a drag-
Ax longitudinal distance from the quarter point of the mean aero-
dynamic chord to a more rearward moment center
y lateral distance from the plane of symmetry
a angle of attack of the wing chord at the plane of symmetry
(referred to herein as the wing-root chord)
at angle of attack of the tail
0 propeller-blade angle measured at 0.70 tip radius
o' propeller-blade-section angle
e effective downwash angle
8 flap angle, measured relative to the local chord in planes
normal to the reference sweep line
Propeller or propulsive efficiency
flt - tail-efficiency factor (ratio of the lift-curve slope of the
I horizontal tail when mounted on the model to the lift-curve
slope of the isolated horizontal tail)
p mass density of air
-~--~---5~C~C-- ~CFC -
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Edwards, George G.; Buell, Donald A.; Demele, Fred A. & Sutton, Fred B. Analysis 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/metadc56014/m1/6/: accessed May 27, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.