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Rotation applies to tricycle gear aircraft rather than those with conventional gear (tailwheel aircraft). The on-ground angle of attack of the wing has to be established during the design phase. The main and nose-gear leg lengths are chosen to give a negative angle of attack relative to the ground.
The three axes of rotation in an aircraft. 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.
The position of all three axes, with the right-hand rule for describing the angle of its rotations. An aircraft in flight is free to rotate in three dimensions: yaw, nose left or right about an axis running up and down; pitch, nose up or down about an axis running from wing to wing; and roll, rotation about an axis running from nose to tail.
Sets of rotation axes associated with both proper Euler angles and Tait–Bryan angles are commonly named using this notation (see above for the six possibilities for each). If each step of the rotation acts on the rotating coordinate system XYZ, the rotation is intrinsic (Z-X'-Z''). Intrinsic rotation can also be denoted 3-1-3.
Rotation speed. The speed at which the pilot begins to apply control inputs to cause the aircraft nose to pitch up, after which it will leave the ground. [7] [26] [Note 1] V rot: Used instead of V R (in discussions of the takeoff performance of military aircraft) to denote rotation speed in conjunction with the term V ref (refusal speed). [19 ...
Heading, elevation and bank angles (Z-Y’-X’’) for an aircraft. The aircraft's pitch and yaw axes Y and Z are not shown, and its fixed reference frame xyz has been shifted backwards from its center of gravity (preserving angles) for clarity.
A yaw rotation is a movement around the yaw axis of a rigid body that changes the direction it is pointing, to the left or right of its direction of motion. The yaw rate or yaw velocity of a car, aircraft, projectile or other rigid body is the angular velocity of this rotation, or rate of change of the heading angle when the aircraft is horizontal.
The effect of angular velocity is mainly to decrease the nose lift and increase the tail lift, both of which act in a sense to oppose the rotation. is therefore always negative. There is a contribution from the wing, but since missiles tend to have small static margins (typically less than a calibre), this is usually small.