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: 97 of 171
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.4 -----toil off dz T I 0.20 .I ' /IliL 1 "t tt
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.t 6 - - p-
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PitchIng-moment coeffclent, 4,
Figure 29.- The effects of tail height on the pitching-moment characteristics of the model;
flaps up; M = 0.123; R = 4,000,000; p = 310; it = m4o.
.20 ./6 ./1 .08 .04 0 -04 -W .12
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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/m1/97/: accessed May 20, 2019), University of North Texas Libraries, Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.