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: 94 of 171
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-H Inboord propeler
I Ouboord propeller only H-
-- popllers off
/ncrenments n hCm due
At oddin of potr:
.-- norImWol nfo
- -- -stu
A Om l
i fri g t r
.06 .04 O -04 -.O -. ./6 .12
P/kching-moment coeffitcent, Cma,
o -0409 -12 96 -:20 -,24 ,-f
(a) Te 0.40
Figure 28.- A coqarison 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;
inboard Claps deflected; M= 0.082; B - 4000,000oo, = 260; it = 0
Jm . . . . . . .
i i i i i i 1 -1 1 -, 1 1 1 - , , i 4-
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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/m1/94/: accessed May 20, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.