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: 56 of 171
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NACA TN 3790
5000 hp per engine
.06 - --
0 .2 .4 .6 .8 /.0
Lift coefficient, CL
Figure 9.- The Tc vs. CL relationship for simulated high-speed full-
scale constant power conditions; wing loading = 75 lb/sq ft; propeller
rotational speed = 1715 rpm; propeller diameter = 14 ft; assumed
propeller efficiency = 0.65; altitude = 40,000 ft.
Cc~C~CC- -------- -- -C
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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/m1/56/: accessed May 19, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.