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: 67 of 171
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NAA TN 3790
ACL wing .1
.T= O. 80
Inboord propeller only ..6P
Outboard propeller only .60
- - ".0
Angle of attack, a, deg
(a) FlapB up.
Figure 16,- The increments .of lift coefficient due to the slipstreams on
the wing; M = 0.082; R = 4,000,000; 0 = 260.
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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/m1/67/: accessed May 22, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.