Performance, stability, dynamics, and control of airplanes
This book provides a comprehensive and integrated exposure to airplane performance, stability, dynamics, and flight control. It supports a two-semester course for senior undergraduate or first-year graduate students in aerospace engineering. Basic aerodynamics, dynamics, and linear control systems are presented to help the reader grasp the main subject matter. In this text, the airplane is assumed to be a rigid body--elastic deformations and their effects on airplane motion are not considered. Numerous solved examples illustrate theory and design methods. Several exercise problems with answers are included in each chapter to help the reader acquire problem-solving skills. In addition, MATLAB tools are used for the control design. In the second edition, lists of symbols/nomenclature and tables of important formulas are included to facilitate the reader.
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Review of Basic Aerodynamic Principles
Static Stability and Control
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aerodynamic center aileron aircraft airfoil altitude angle of attack angular velocity approximately aspect ratio assume aviation airplane axes system axis center of gravity characteristic equation climb closed-loop damping ratio deflection delta wing derivatives dihedral directional stability disturbance drag coefficient dynamic effect elevator estimated Euler angles feedback flight velocity flow separation forebody frequency fuselage given by Eq high angles horizontal tail increases induced drag inertia input ISBN Laplace transform lateral-directional leading edge leading-edge level flight lift coefficient lift-curve slope load factor longitudinal Mach number matrix maximum method motion Nyquist plot obtain parameter phase-variable form phugoid pitch plane poles positive pressure rad/s response Reynolds number root chord root-locus rudder s-plane Schematic sections short-period shown in Fig side force sideslip spin stall static steady-state stick force strip theory subsonic speeds supersonic speeds surface thrust transfer function unit-step variation vertical tail vortex breakdown wing rock zero