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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 382
382 Flight Dynamics Principles
Equating equivalent terms in equation (13.219), expressions for the normalised
pitching moment derivatives, referred to aircraft wind axes, may be derived as
follows:
M
u
=
ρS
c
2I
y
(V
2
C
m
)
U
=
ρVS
c
2I
y
V
C
m
V
+2C
m
ρVS
c
2I
y
M
C
m
M
+2C
m
=
ρVS
c
2I
y
(MC
m
M
+2C
m
) (13.220)
Again, remembering that for a wind axes reference U =U
e
+u V and Mach
number M =V /a. To define the derivative M
u
at the flight condition of interest, let the
perturbation become vanishingly small such that u 0, hence V V
0
and M M
0
.
Further, since the perturbation is a disturbance about trim and when the aircraft is in
trim the pitching ...
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Publisher Resources

ISBN: 9780750669276