Flight dynamics (fixed-wing aircraft) | Wikipedia audio article
Channel: wikipedia tts
Date: 2019-06-04

This is an audio version of the Wikipedia Article:
https://en.wikipedia.org/wiki/Flight_dynamics_(fixed-wing_aircraft)


00:01:58 1 Introduction
00:02:08 1.1 Reference frames
00:09:08 1.2 Design cases
00:10:33 2 Forces of flight
00:10:49 2.1 Aerodynamic force
00:10:59 2.1.1 Components of the aerodynamic force
00:13:19 2.1.2 Aerodynamic coefficients
00:17:56 2.1.3 Dimensionless parameters and aerodynamic regimes
00:22:00 2.1.4 Drag coefficient equation and aerodynamic efficiency
00:28:57 2.1.5 Parabolic and generic drag coefficient
00:32:05 2.1.6 Variation of parameters with the Mach number
00:33:50 2.1.7 Aerodynamic force in a specified atmosphere
00:34:27 3 Static stability and control
00:34:36 3.1 Longitudinal static stability
00:34:48 3.2 Directional stability
00:34:53 4 Dynamic stability and control
00:35:04 4.1 Longitudinal modes
00:35:17 4.1.1 Short-period pitch oscillation
00:35:24 4.1.2 Phugoid
00:36:07 4.2 Lateral modes
00:36:18 4.2.1 Dutch roll
00:36:58 4.2.2 Lateral and longitudinal stability derivatives
00:52:52 4.2.3 Equations of motion
01:00:01 4.2.4 Roll subsidence
01:00:54 4.2.5 Spiral mode
01:07:40 4.2.5.1 Spiral mode trajectory
01:14:44 5 See also
01:26:14 6 References
01:27:30 6.1 Notes
01:27:53 6.2 Bibliography



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SUMMARY
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Flight dynamics is the science of air vehicle orientation and control in three dimensions. The three critical flight dynamics parameters are the angles of rotation in three dimensions about the vehicle's  center of gravity (cg), known as pitch, roll and yaw.
Control systems adjust the orientation of a vehicle about its cg. A control system includes control surfaces which, when deflected, generate a moment (or couple from ailerons) about the cg which rotates the aircraft in pitch, roll, and yaw.  For example, a pitching moment comes from a force applied at a distance forward or aft of the cg, causing the aircraft to pitch up or down.
Roll, pitch and yaw refer to rotations about the respective axes starting from a defined steady flight equilibrium state.  The equilibrium roll angle is known as wings level or zero bank angle.
The most common aeronautical convention defines roll as acting about the longitudinal axis, positive with the starboard (right) wing down. Yaw is about the vertical body axis, positive with the nose to starboard. Pitch is about an axis perpendicular to the longitudinal plane of symmetry, positive nose up.A fixed-wing aircraft increases or decreases the lift generated by the wings when it pitches nose up or down by increasing or decreasing the angle of attack (AOA). The roll angle is also known as bank angle on a fixed-wing aircraft, which usually "banks" to change the horizontal direction of flight. An aircraft is streamlined from nose to tail to reduce drag making it advantageous to keep the sideslip angle near zero, though an aircraft may be deliberately "sideslipped" to increase drag and descent rate during landing, to keep aircraft heading same as runway heading during cross-wind landings and during flight with asymmetric power.