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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
App-2-H6927.tex 20/6/2007 16: 39 Page 412
Appendix 2
Definitions of Aerodynamic Stability and
Control Derivatives
Notes
(i) The derivatives given in TablesA2.5–A2.8 are all referred to generalised body
axes and, U
e
=V
0
cos θ
e
and W
e
=V
0
sin θ
e
. In the particular case when the
derivatives are referred to wind axes θ
e
=0 and the following simplifications
can be made, U
e
=V
0
, W
e
=0, sin θ
e
=0 and cos θ
e
=1.
(ii) The equivalent algebraic expressions in Tables A2.5–A2.8 were derived with
the aid of the computer program Mathcad which includes a facility for
symbolic calculation.
(iii) In Tables A2.5–A2.8 normalised mass and inertias are used which are defined
as follows:
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Publisher Resources

ISBN: 9780750669276