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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
Ch08-H6927.tex 20/6/2007 16: 35 Page 216
216 Flight Dynamics Principles
with their equivalent expressions. Then, after some re-arrangement equation (8.16)
may be written:
C
m
+δC
m
=
C
m
0
+C
L
w
(h h
0
) V
T
C
L
w
a
1
a
1
dε
dα
+a
1
η
T
+a
2
η + a
3
β
η

+
δC
L
w
(h h
0
) V
T
δC
L
w
a
1
a
1
dε
dα
+
δC
L
w
a
1
l
T
μ
1
c
+a
2
δη

(8.17)
Now in the steady equilibrium flight condition about which the manoeuvre is executed
the pitching moment is zero therefore
C
m
= C
m
0
+C
L
w
(h h
0
) V
T
C
L
w
a
1
a
1
dε
dα
+a
1
η
T
+a
2
η + a
3
β
η
= 0
(8.18)
and equation (8.17) simplifies to that describing the incremental pitching moment
coefficient:
δC
m
= δC
L
w
(h h
0
) V
T
δC
L
w
a
1
a
1
dε
dα
+
δC
L
w
a
1
l
T
μ
1
c
+a
2
δη
(8.19)
8.4 LONGITUDINAL MANOEUVRE ...
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Publisher Resources

ISBN: 9780750669276