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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 371
Aerodynamic Stability and Control Derivatives 371
By definition, the yawing moment due to the fin in a yaw rate perturbation is given by
r
N
r
(fin)
= N
fin
=−
1
2
ρV
0
S
F
l
2
F
a
1
F
r (13.165)
Whence, the expression for the fin contribution to the dimensional yawing moment
due to yaw rate derivative is
N
r
(fin)
=−
1
2
ρV
0
S
F
l
2
F
a
1
F
(13.166)
As before, and with reference toAppendix 2, the dimensionless form of the derivative
is given by
N
r(fin)
=
N
r
(fin)
1
2
ρV
0
Sb
2
=−a
1
F
V
F
l
F
b
=−
l
F
b
N
v(fin)
(13.167)
The fin volume ratio
V
F
is given by equation (13.109). The total value of the yawing
moment due to yaw rate derivative is therefore given by the sum of all the ...
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Publisher Resources

ISBN: 9780750669276