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- Category: Dynamics of. Atmospheric Flight (continued)
- COUPLING OF CONTROLS WITH ELASTIC DEGREES OF FREEDOM
- THE SERVO EQUATION
- INERTIAL COUPLING
- EQUATIONS OF MOTION
- THE KINETIC ENERGY T
- EQUATIONS OF MOTION OF THE CONTROL SYSTEMS
- CHANGE OF FLIGHT-PATH ANGLE
- EXAMPLE—SUPPRESSION OF THE PHUGOID
- Closed-loop control
- NUMERICAL EXAMPLE—PITCH/ROLL COUPLING OF A SMALL AIRPLANE
- WHEN Cm<t > 0 (AERODYNAMICALLY UNSTABLE CONFIGURATION)
- INERTIAL COUPLING IN RAPID MANEUVERS
- TRANSIENT RESPONSE TO AILERON AND RUDDER
- DUTCH-ROLL APPROXIMATION
- APPROXIMATE LATERAL TRANSFER FUNCTIONS
- LATERAL FREQUENCY RESPONSE
- NUMERICAL EXAMPLE
- THE STEADY TURN
- LATERAL STEADY STATES
- NUMERICAL EXAMPLE—STEP RESPONSE
- RESPONSE TO THE THROTTLE
- NUMERICAL EXAMPLE—STEP RESPONSE
- NUMERICAL EXAMPLE—FREQUENCY RESPONSE
- PHUGOID APPROXIMATION
- SHORT-PERIOD APPROXIMATION
- RESPONSE TO ELEVATOR INPUT
- LATERAL CONTROL
- LONGITUDINAL CONTROL
- LONGITUDINAL CHARACTERISTICS OF A STOL AIRPLANE
- EFFECT OF SPEED DERIVATIVES
- EFFECT OF STATIC MARGIN
- EFFECT OF VERTICAL DENSITY-GRADIENT
- EFFECT OF FLIGHT-PATH ANGLE
- EFFECT OF ALTITUDE
- EFFECT OF FLIGHT CONDITION ON THE LONGITUDINAL MODES OF A SUBSONIC JET TRANSPORT
- GENERAL THEORY OF STATIC LONGITUDINAL STABILITY
- This also is compared with exact results in the figures that follow. SHORT-PERIOD MODE
- PHUGOID MODE
- APPROXIMATE EQUATIONS FOR THE LONGITUDINAL MODES
- FLIGHT PATHS IN THE CHARACTERISTIC MODES
- EIGENVECTORS
- EIGENVALUES
- APPROXIMATION
- Stability of steady flight
- THE DERIVATIVE
- THE DERIVATIVE C„r
- THE r DERIVATIVES (Cv Cv C„r, C*0r, Chr)
- THE DERIVATIVE CA(tji
- THE DERIVATIVE C
- THE DERIVATIVE Сц
- THE DERIVATIVE C„
- THE p DERIVATIVES (Cv Cv C„s, C7la/ Chr)
- INFLUENCE OF FIN ON Clf
- INFLUENCE OF SWEEP ON Ct
- INFLUENCE OF FUSELAGE ON Сц
- THE DERIVATIVE C
- THE f} DERIVATIVES (C,,f C,,f C„,, CAr)
- AILERON REVERSAL
- ROLLING CONTROL
- ROLL STIFFNESS
- YAW CONTROL
- YAW STIFFNESS (WEATHERCOCK STABILITY)
- Lateral aerodynamic characteristics
- SUMMARY OF THE FORMULAE
- FORCES ON THE WING
- THE z DERIVATIVES (Сг., CA, Cw Cm)
- AERODYNAMIC TRANSFER FUNCTIONS
- CONTRIBUTIONS OF A TAIL
- THE a DERIVATIVES (CL„ Стл> QJ
- PITCH DAMPING OF PROPULSIVE JETS
- CONTRIBUTIONS OF A WING
- CONTRIBUTIONS OF A TAIL
- THE q DERIVATIVES (Cw Cm,, Che)
- THE DERIVATIVES Cw Cmy, Chey
- 7.8 THE V DERIVATIVES (CTv, CDy, CLp, Cmr, Chep)
- THE FORWARD LIMIT
- C. G. LIMITS
- GROUND EFFECT
- EFFECT OF STRUCTURAL FLEXIBILITY
- . THE INFLUENCE OF JET ENGINES
- EFFECTS ON THE TAIL
- THE INFLUENCE OF RUNNING PROPELLERS
- INFLUENCE OF THE PROPULSIVE SYSTEM ON TRIM AND PITCH STIFFNESS
- INFLUENCE OF HIGH-LIFT DEVICES ON TRIM AND PITCH STIFFNESS
- EFFECT UPON CONTROL FORCE TO TRIM AND h'„
- Longitudinal aerodynamic characteristics—part 2
- MANEUVERABILITY—ELEVATOR ANGLE AND CONTROL FORCE PER g
- CONTROL FORCE GRADIENT
- CONTROL FORCE TO TRIM
- SERVO TABS
- SPRING TABS
- GEARED TABS
- THE USE OF TABS
- CONTROL-FREE NEUTRAL POINT
- FREE-ELEVATOR FACTOR
- INFLUENCE OF A FREE ELEVATOR ON LIFT AND MOMENT
- CONTROL HINGE MOMENT
- STATIC STABILITY LIMIT, hs
- VARIATION OF de WITH SPEED
- . ELEVATOR ANGLE TO TRIM