Skip to Main Content
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
Ch06-H6927.tex 20/6/2007 16: 34 Page 152
152 Flight Dynamics Principles
In the initial steady trim state the lift and weight are in balance thus
L
e
=
1
2
ρV
2
0
SC
L
= mg (6.24)
and in disturbed flight the lift is given by
L =
1
2
ρV
2
SC
L
(6.25)
As a consequence of assumption (iii) the lift coefficient C
L
also remains constant and
equations (6.23)–(6.25) may be combined to give
L = mg ρghSC
L
(6.26)
Since simple undamped oscillatory motion is assumed, a consequence of assumption
(ii), the single degree of freedom equation of motion in height may be written:
m
¨
h = L cos θ mg
=
L mg (6.27)
since, by definition, θ is a small angle. Substituting for lift L from equation
Become an O’Reilly member and get unlimited access to this title plus top books and audiobooks from O’Reilly and nearly 200 top publishers, thousands of courses curated by job role, 150+ live events each month,
and much more.
Start your free trial

You might also like

Commercial Airplane Design Principles

Commercial Airplane Design Principles

Pasquale M. Sforza
Theory and Practice of Aircraft Performance

Theory and Practice of Aircraft Performance

Ajoy Kumar Kundu, Mark A. Price, David Riordan

Publisher Resources

ISBN: 9780750669276