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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 350
350 Flight Dynamics Principles
M
˙w
=
M
˙w
Pitching moment due to rate of change of normal velocity
In this instance the pitching moment is assumed to arise entirely from the moment of
the tailplane normal force perturbation about the cg resulting from the perturbation
in incidence, given by equation (13.64). Thus, in the perturbation
M = Zl
T
=−
1
2
ρV
2
S
T
l
T
C
L
T
∂α
T
α
T
(13.73)
Again, by definition
M =
M
˙w
˙w (13.74)
and in the limit V
=
V
0
. Thus substitute equation (13.64) into (13.73) and apply
equation (13.74) to obtain
M
˙w
=−
1
2
ρS
T
l
2
T
a
1
dε
dα
(13.75)
and with reference toAppendix 2, the dimensionless form of the derivative
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Publisher Resources

ISBN: 9780750669276