Effects of Various Modifications on the Static Longitudinal Stability and Control Characteristics of a 0.065-Scale Model of the Chance Vought Regulus II Missile at a Mach Number of 2.01 Page: 4 of 28
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f .. f W211. r,"* ***9
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0 *
* 00
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** *be
L/D
m/mo
Subscripts:
trim
R
Lelevon deflection normal to hinge line, deg
lift-drag ratio, CL/CD
mass-flow ratiomeasured for
Cm = 0
right
leftflL
Z
q
M
S
Sc
Sw
b
c
a
t
x
80force along Z-axis
moment about Y-axis
free-stream dynamic pressure
Mach number
wing area including body intercept, 88.47 sq in.
exposed area of canard surface
ratio of exposed area of canard to total wing area
wing span, 15.63 in.
chord, in.
wing mean geometric chord, 5.78 in.
angle of attack of fuselage center line, deg
airfoil thickness, in.
chordwise distance from leading edge of airfoil section, in.
canard deflection with respect to fuselage center line, deg:e
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: ;NACA RM SL551
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Robinson, Ross B. & Driver, Cornelius. Effects of Various Modifications on the Static Longitudinal Stability and Control Characteristics of a 0.065-Scale Model of the Chance Vought Regulus II Missile at a Mach Number of 2.01, report, September 26, 1955; (https://digital.library.unt.edu/ark:/67531/metadc53019/m1/4/: accessed April 24, 2024), University of North Texas Libraries, UNT Digital Library, https://digital.library.unt.edu; crediting UNT Libraries Government Documents Department.