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: 91 of 171
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I Inboord propeller I
Spr peller on FH>-- '
016 l -I l I I
./6 ./2 0 .04
_ - -l LLIIill IIt I I TIIYI I ]
0 -.04 06 12 ./6 .12
.04 0 -04 .08
Increments in Cn due
S ddn oflW pof er:
12 It/6dC *6 sa24
Ich1ng-moment coefficient, Cm a0
(a) T. = 0-.40
Figure 27.- A comparison of the various effects of the inboard propeller on the pitching-moment
characteristics of the model with those of the outboard propeller; tail height = 0.10 b/2;
flaps up; M = 0.082; R = 4,000,000; = 260; it = 40o
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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/m1/91/: accessed May 25, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.