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: 55 of 171
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.7 r. . - I -- ' -II I I... II
_ _:"_ .
I J . ..
S ___000 p per ang
Lift coefficient, CL
Figure 8,- The T , vs. . relationship for simulated take-off full-scale constant
conditions; wing lo 1ing 100 Ib/sq ft; propeller rotational speed = 1715 rpm;
diameter = 14 ft; propeller efficiency and blade angle as show; sea level.
0r /00 200 3 %
v and 4, derved from ref 5 for /0,000 lhp
10,000 hp per engine-
- F-1.I. 11
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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/m1/55/: accessed May 24, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.