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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 ., o..
40 --. o. . ..~ ' . ; \- 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 www.aero.cn 航空翻译 www.aviation.cn 本文链接地址：PERFORMANCE, STABILITY, DYNAMICS, AND CONTROL1
