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Static Stability and Control
Equations of Motion and Estimation
A Brief Review
Airplane Response and ClosedLoop Control
Inertia Coupling and Spin
Stability and Control Problems at High Angles
Appendix A Standard Atmospheres
aerodynamic center aileron aircraft airfoil altitude angle of attack angular velocity approximation aspect ratio assume aviation airplane axis center of gravity characteristic equation climb closed-loop configuration 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 pitching moment plane poles positive pressure rad/s response Reynolds number root chord root-locus rudder s-plane sections short-period shown in Fig side force sideslip spin stall static steady-state stick force strake strip theory subsonic speeds supersonic speeds surface thrust transfer function unit-step variation vertical tail vortex breakdown wing rock zero
Page 12 - The minimum pressure is at 0.5c. 3 — The drag coefficient is near its minimum value over a range of lift coefficients of 0.3 above and below the design lift coefficient. 4 — The design lift coefficient is 0.4. 21 — The maximum thickness is 0.21c.
Page 1 - Kn < 0.1. The Knudsen number can be expressed in terms of other important dimensionless parameters in fluid mechanics. The Reynolds number is the ratio of inertial forces to viscous forces Re=^— (4.4) where va is a characteristic velocity and v is the kinematic viscosity of the fluid.