A Flight Investigation of the Handling Characteristics of a Fighter Airplane Controlled Through an Attitude Type of Automatic Pilot Page: 4 of 62
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NACA RM L56A12
K pendulum gain, volts/g
Ke pitch vertical gyro gain, volts/radian
K* pitch rate gyro gain, volts/radian/sec
K1 roll vertical gyro gain, volts/radian
K roll rate gyro gain, volts/radian/sec
K4 directional gyro gain, volts/radian
K yaw rate gyro gain, volts/radian/sec
M Mach number
p rolling velocity, radian/sec
q pitching velocity, radian/sec
r yawing velocity, radian/sec
R servo system input signal, volts (used in ground tests)
Vi indicated airspeed, knots
a angle of attack, deg
0 angle of sideslip, deg
6aT total aileron deflection, deg
6c automatic-pilot control stick deflection, lateral, deg
6Cp automatic-pilot control stick deflection, fore and aft, deg
be elevator deflection, deg
br rudder deflection, deg
5s servo drum rotation, deg
0 angle of pitch, degI-
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Sjoberg, S. A.; Russell, Walter R. & Alford, William L. A Flight Investigation of the Handling Characteristics of a Fighter Airplane Controlled Through an Attitude Type of Automatic Pilot, report, April 10, 1956; (https://digital.library.unt.edu/ark:/67531/metadc62632/m1/4/: accessed April 25, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.