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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 365
Aerodynamic Stability and Control Derivatives 365
By definition the total yawing moment due to roll rate is given by
p
N
p
= N
total
=
'
semi
span
δN
total
=−ρV
0
p
'
s
0
a
y
α
e
dC
D
dα
y
c
y
y
2
dy (13.135)
Whence, the expression for the dimensional derivative
N
p
=−ρV
0
'
s
0
C
L
y
dC
D
dα
y
c
y
y
2
dy (13.136)
where C
L
y
=a
y
α
e
is the equilibrium local lift coefficient. With reference to
Appendix 2, the dimensionless form of the derivative is given by
N
p
=
N
p
1
2
ρV
0
Sb
2
=−
1
2Ss
2
'
s
0
C
L
y
dC
D
dα
y
c
y
y
2
dy (13.137)
13.3.4 Derivatives due to rate of yaw
As seen by the pilot, a positive yaw rate is such that the nose of the aeroplane swings
to the right and the small ...
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Publisher Resources

ISBN: 9780750669276