Wing Pressure Distributions Over the Lift Range of the Convair XF92A Delta-Wing Airplane at Subsonic and Transonic Speeds Page: 47 of 137
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NACA RM H55G07
TABLE VI. - Continued
PRESSURE COEFFICIENTS AND AERODYNAMIC CHARACTERISTICS
OF THE CONVAIR XF-92A WING
[Wind-up turn; M = 0.91 to 0.84](j) M = 0.85
CNA = 0.41a = 9.50
eL = 5.60 upPressure coefficients
ice Rw A Row B Row C Row D Row E
Orifice
Upper Lower Upper Lower Upper Lower Upper Lower Upper Lower
surface surface surface surface surface surface surface surface surface surface
1 -0.365 -0.9----- ,952 -134 ----- -1.226 ----- -0.561
2 -.730 0.451 -1.14 0.352 -.952 0.261 -1.030 ----- -.600 -0.013
3 -.634 .o4 -1.121 .300 -.991 .248 -1.0 56 0.248 -.274 -.091
4 -.574 .378 -1.134 .248 -1.017 .229 -1.134 .222 -.214 -.183
5 -.417 .313 -1.239 ---- -1.116 .123 -1.108 .170 -.222 -.209
6 -.391 .261 -1.154 .2355 -1.030 .078 -1.08 .149 -.222 --143
7 -.391 .261 -.40 -. 965 .039 -.913 .117 -.222 -.196
8 -.365 .209 -.391 -.8048 -.026 -.821 .026
9 -.313 .143 -.404 .104 -.326 -.o026 -.665 -.183
o10 -.313 .209 -.417 .052 .034 -.o6o -. 535 -.196
11 -.339 .170 -.482 -.065 .170 -.462 -.73o
12 -.430 .078 -.613 -.130 .27 -.821 -.292 -.300
13 -.378 .052 -.104 -.052 .183 -.235 -.321 -.104
14 -.482 ----- .039 -.052 .117 .013 -.274 -.052
15 -.391 -.021 .274-
16 -.496 -.104 .104 -.104
17 -.535 -.143 .091 .005
18
19 ---- -
20 -.o78 -.086
21 -.013 -.535
22 .052 -.143
23 .o65 -.02146
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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/m1/47/: accessed March 30, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.