Flight evaluation of the lateral stability and control characteristics of the Convair YF-102 airplane Page: 4 of 40
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NACA RM H56Gll 3
IX moment of inertia about longitudinal body axis, slug-ft2
I e moment of inertia of rotating engine parts about X-body axis,
slug-ft2
Iy moment of inertia about lateral body axis, slug-ft2
IZ moment of inertia about normal body axis, slug-ft2
IXZ product of inertia referred to X- and Z-axis, slug-ft2
M Mach number
P period, sec
p rolling angular velocity, radians/sec
rolling angular acceleration, radians/sec2
average rolling velocity, radians/sec
pitching angular velocity, radians/sec
pitching angular acceleration, radians/sec2
r yawing angular velocity, radians/sec
r yawing angular acceleration, radians/sec2
S wing area, ft2
T1/2 time to damp to one-half amplitude, sec
t time, sec
tW=90o time to bank to 900, sec
V true velocity, ft/sec
Ve equivalent velocity, Vp r, ft/sec
Vi indicated velocity, mph
ve equivalent side velocity, - , ft/e
5 f/se
a I- -
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Sisk, Thomas R.; Andrews, William H. & Darville, Robert W. Flight evaluation of the lateral stability and control characteristics of the Convair YF-102 airplane, report, January 16, 1957; (https://digital.library.unt.edu/ark:/67531/metadc62560/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.