Drag and Longitudinal Trim at Low Lift of the North American YF-100A Airplane at Mach Numbers from 0.76 to 1.77 as Determined from the Flight Test of a 0.11-Scale Rocket Model Page: 4 of 25
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NACA RM SL53Ella
a angle of attack, deg
Cmc rate of change of pitching-moment coefficient with angle of
P period of the short-period longitudinal oscillation, sec
C + C. pitch-damping parameter - + - per radian
q Oc ac
a da, radians/sec
C rate of change of lift coefficient with angle of attack
dCL/dz per degree
V velocity, ft/sec
t time, sec
9 flight-path angle
p free-stream static pressure, lb/sq ft
p density of air, slugs/cu ft
A cross-sectional area, sq ft
Z model length from nose to fuselage base, 5.248 ft
x distance measured rearward from the nose, ft
r radius, ft
a1/g longitudinal accelerometer reading
an/g normal accelerometer reading
T1/2 time required for the short-period longitudinal oscillation
to damp to one-half amplitude
Iy mass moment of inertia of the model about the pitch axis
(7.72 and 7.42 slug-ft2 before and after sustainer rocket
C ONF IDENT IAL
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Blanchard, Willard S. Drag and Longitudinal Trim at Low Lift of the North American YF-100A Airplane at Mach Numbers from 0.76 to 1.77 as Determined from the Flight Test of a 0.11-Scale Rocket Model, report, January 1, 1953; (digital.library.unt.edu/ark:/67531/metadc65341/m1/4/: accessed December 17, 2017), University of North Texas Libraries, Digital Library, digital.library.unt.edu; crediting UNT Libraries Government Documents Department.