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Flight Dynamics Principles, 2nd Edition
book

Flight Dynamics Principles, 2nd Edition

by Michael V. Cook
February 2011
Beginner to intermediate content levelBeginner to intermediate
488 pages
17h 21m
English
Butterworth-Heinemann
Content preview from Flight Dynamics Principles, 2nd Edition
Ch13-H6927.tex 30/6/2007 11: 47 Page 377
Aerodynamic Stability and Control Derivatives 377
and, with reference to Appendix 2, an expression for the dimensionless derivative
may be written
L
ζ
=
L
ζ
1
2
ρV
2
0
Sb
=
S
F
h
F
Sb
a
2
R
V
F
h
F
l
F
a
2
R
(13.200)
where
V
F
is the fin volume ratio.
N
ζ
=
N
∂ζ
Yawing moment due to rudder
This derivative describes the yaw control property of the aeroplane and, again, an
accurate estimate of its value is important to flight dynamics analysis. Since the side
force due to rudder acts well behind the cg it generates a yawing moment described
as follows:
N
ζ
ζ =−Yl
F
=−
1
2
ρV
2
S
F
l
F
a
2
R
ζ (13.201)
Thus, the simple expression for the dimensional derivative is ...
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Publisher Resources

ISBN: 9780750669276