Wing Pressure Distributions Over the Lift Range of the Convair XF92A Delta-Wing Airplane at Subsonic and Transonic Speeds Page: 88 of 137
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B Static Ob
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(a) cA = 0.11; a. = 3.4; BeL = 1.90 u; M = 0.67.
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x/c
(b) CNA1 0.21; a = 6.40; 8eL = 2.80 up; M m 0.50.
Figure 4.- Pressure distribution over the wing at five semispan stations
for several values of airplane normal-force coefficient. Stall approach.
XF-92A airplane.>
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Keener, Earl R. & Jordan, Gareth H. Wing Pressure Distributions Over the Lift Range of the Convair XF92A Delta-Wing Airplane at Subsonic and Transonic Speeds, report, November 30, 1955; (https://digital.library.unt.edu/ark:/67531/metadc61544/m1/88/: accessed April 25, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.