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: 4 of 171
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NACA TN 3790
A upflow angle, average angle of local flow at the 0.7 prQpeller
radius on the horizontal center line of the propeller plane,
measured with respect to the thrust axis in a plane parallel
to the plane of symmetry
a mean-line designation, fraction of chord over which design load
a' normal acceleration
at lift-curve slope of the isolated tail
aw lift-curve slope of the model, tail off
b/2 wing semispan perpendicular to the plane of symmetry
b' propeller-blade width
CL lift coefficient, qS
C1 rolling-moment coefficient,
rolling moment (for complete airplane)
Cm pitching-moment coefficient about the quarter point of the wing
mean aerodynamic chord, itching moment
Cmcg pitching-moment coefficient about the center of gravity,
pitching moment (See fig. i(a).)
CN propeller normal-force coefficient,
yawing moment (for complete airplane)
Cn yawing-moment coefficient,
Op power coefficient,
CPtotal sum of the power coefficients for both propellers
CT thrust coefficient, n
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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/m1/4/: accessed April 25, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.