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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
Ch12-H6927.tex 20/6/2007 16: 38 Page 323
Aerodynamic Modelling 323
where the total perturbation velocity component along the x axis is given by
U = U
e
+u V
0
+u V (12.5)
Whence,
X
u
=−
D
V
(12.6)
and the slope of the drag–velocity plot at p gives the quasi-static value of the derivative
X
u
at the flight condition corresponding with the trimmed velocity V
0
. Some further
simple analysis is possible since the drag is given by
D =
1
2
ρV
2
SC
D
(12.7)
and assuming the air density ρ remains constant, since the perturbation is small, then,
D
V
=
1
2
ρVS
2C
D
+V
C
D
V
(12.8)
To define the derivative
X
u
at the flight condition of interest, let the perturbation
become vanishingly ...
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Publisher Resources

ISBN: 9780750669276