Effects of a Fuselage on the Aerodynamic Characteristics of a 42 Degree Sweptback Wing at Reynolds Numbers to 8,000,000 Page: 4 of 34
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NACA PM No. L7E13
Reynolds number (pYV/j)
free-stream Mach number (V/a)
angle of attack measured in plane of symmetry, degrees
angle of yaw, positive when right' wing is back, degrees
rate of change of rolling-moment ooefficient with angle
of yaw, per degree (01/*)
rate of change of yawing-moment coefficient with angle
of yaw, per degree ( c/CnZ)
rate of change of lateral-force coefficient with angle
of yaw, per degree (C0y/4)
increment in CZ
rate of change of pitching-moment coefficient with lift
drag = -X at zero yaw
mean aerodynamic chord measured parallel to plane of
symmetry (sj c2 dy)
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Salmi, Reino J.; Conner, D. William & Graham, Robert R. Effects of a Fuselage on the Aerodynamic Characteristics of a 42 Degree Sweptback Wing at Reynolds Numbers to 8,000,000, report, June 10, 1947; (digital.library.unt.edu/ark:/67531/metadc64565/m1/4/: accessed January 22, 2019), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.