Additional Results on the Static Longitudinal and Lateral Stability Characteristics of a 0.05-Scale Model of the Convair F2Y-1 Airplane at High Subsonic Speeds Page: 4 of 113
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NACA RM SL54H05 CONFIDENTIAL 3
Cn yawing-moment coefficient, Yawing moment
qSb
Cy lateral-force coefficient, Lateral force
qS
q dynamic pressure, pV2/2, lb/sq ft
S wing area, 1.42 sq ft
b/2
c mean aerodynamic chord of wing, , c2dy, 1.069 ft
c local wing chord, parallel to plane of symmetry, ft
b wing span, 1.76 ft
p air density, slugs/cu ft
V free-stream velocity, ft/sec
M Mach number
R Reynolds number of wing based on E
a angle of attack of fuselage reference line, deg
P angle of sideslip, deg
5 control surface deflection, deg
pb/2V wing-tip helix angle, radians
p rolling velocity, radians/sec
Czp =-, per radian
P ~pb
c--
2V
L/D lift-drag ratio
Subscripts:
b base of model fuselage
e elevon
CONFIDENTIAL
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Spreeman, Kenneth P. & Few, Albert G., Jr. Additional Results on the Static Longitudinal and Lateral Stability Characteristics of a 0.05-Scale Model of the Convair F2Y-1 Airplane at High Subsonic Speeds, report, August 10, 1954; (https://digital.library.unt.edu/ark:/67531/metadc65304/m1/4/: accessed April 23, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.