282
PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL
a) Zero rudder deflection
b) With rudder deflection
R
U
n
w
a
y
R
U
n
w
a
y
ng.3.8s Schematic diagramofcrosswind takeoffflamLing
;/
. .':
STATIC STABILITY AND CONTROL
r:
\
\
\
\V .d
┏━━━┳━━━━━━━┓
┃ ┃ \ ┃
┃ ┃L ┃
┃ ┣━━━━━━━┫
┃---- ┃ ┃
┃(, ┃ I ┃
┗━━━┻━━━━━━━┛
Fig.3.86 Adverse yaw during a coordinated turn.
283
these conditions. To break out of an established spin, the rudder must be capable of
producing sufficient yawing moment to slow the spin rate and initiate a successful
recovery. We will learn more about'spin recovery when we discuss the spinning
motion in Chapter 7.
3.5.6 Rudder-Fr€e Directional Stallu7ity
8r f
~g p ,8
T2 <Ti
Fig.3.87 Asymmetric power effects.
(3.322)
In sideslipping motion, if the rudder is left free to float (pilot's foot off the
rudder pedal), it will assume a condition such that the net hinge moment is zero.
This position is called the floating angle of the rudder and is grven by
. AIAA
EDUCATION
SERIES
.,
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40
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' . ; \-
TL671,4
.P28
Performance, Stability, Dynamics9
and Control of Airplanes
Performance, Stability, Dynam.ics,
and Control of Airplanes
Bandu N. Pamadi
NASA Langley Researcb Center
Hampton, Mrginia
EDUCATION SERIES
J. S. Przemieniecki
Series Editor-in-Chief
Air Force Institute of Technology
Wright-Patterson Air Force Base, Ohio
Published by
American Institute of Aeronautics and Astronautics, Inc.
1801 Alexander Bell Drive, Reston, VA 20191
317385
-':.-I-- 1.,:' 1 i ,
" e: 'i_.
American Institute of Aeronautics and Astronautics, Inc., Reston, Virginia
5432
Library ot Congress Cataloging-in-Publication Data
Pamadi, Bandu N., 1945-
Performance, stability, dynamics, and control of airplanes /
p. cm.-(AIAA eduaUion series)
Includes bibliograplucal references and index.
l. Airplanes-Performance.
3. Airplanes-Controlsystems.
II. Series.
2. Stabilityofairplanes.
4. Aerodynamcs. I. Title.
TL671.4.P28 1998 629.13-dc21
ISBN 1-56347-222-8 (alk. paper)
98-34737
aP
MATLAB nu is a registered trademark of The MathWorks, Inc.
Data and information appearing in this book are for informational purposes only. AIAA is
not responsible for any injury or damage resulting from use or reliance, nor does AIAA
warrant that use or reliance will be free from privately owned rights.
This book was written by the author in hi:; private capacity. No official support or endorse-
ment by NASA is intended or should bc inferred.
Foreword
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