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: 70 of 171
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Lt4O 1 i Li
'" propeller -noveie norma force
(a) Flaps up.
Figure 18.- The increments of pitching-moment coefficient of the model due to the normal force
of each propeller, including the effects of slipsream on the nacelle forebody; M = 0.082;
i 4,000,000; p = 260.
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.6040 0 I I 6 .200
i- - I-\ \ I\I I -
Iaa~\l !V 1 1I I I I A_ \N
.0B .06 .04
V/ m - . . - - I --10 1 1 1 1 . -- f- . 1
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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/m1/70/ocr/: accessed June 20, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.