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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 342
342 Flight Dynamics Principles
Z
w
=
Z
W
Normal force due to normal velocity
As before, by differentiating equation (13.9) with respect to W and with reference to
equation (13.24) it may be shown that
Z
w
=
Z
W
=−
1
2
ρV
2
S
C
L
W
+
1
V
C
D
=−
1
2
ρVS
C
L
∂α
+C
D
(13.28)
In the limit equation (13.28) may be rewritten
Z
w
=−
1
2
ρV
0
S
C
L
∂α
+C
D
(13.29)
With reference to Appendix 2, the dimensionless form of the derivative is given by
Z
w
=
Z
w
1
2
ρV
0
S
=−
C
L
∂α
+C
D
(13.30)
13.2.4 Moment derivatives due to velocity perturbations
M
u
=
M
U
Pitching moment due to axial velocity
In a perturbation the pitching moment becomes non-zero and is given by
equation ...
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Publisher Resources

ISBN: 9780750669276