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After rotation, the aircraft continues to accelerate until it reaches its liftoff speed V LO, at which point it leaves the runway. After liftoff, a speed V 2 will be called out, being the speed at which the aircraft is able to climb at a sufficient rate to reach its cruising altitude, and therefore at which the gear will be retracted. [2]
Flight path angle γ: is the angle between horizontal and the velocity vector, which describes whether the aircraft is climbing or descending. Bank angle μ: represents a rotation of the lift force around the velocity vector, which may indicate whether the airplane is turning.
Flight dynamics is the science of air-vehicle orientation and control in three dimensions. The critical flight dynamics parameters are the angles of rotation with respect to the three aircraft's principal axes about its center of gravity, known as roll, pitch and yaw.
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. Axes named according to the air norm DIN 9300
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.
One indicates the rate of turn, or the rate of change in the aircraft's heading; the other part indicates whether the aircraft is in coordinated flight, showing the slip or skid of the turn. The slip indicator is actually an inclinometer that at rest displays the angle of the aircraft's transverse axis with respect to horizontal, and in motion ...
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] V Ref: Landing reference speed or threshold crossing speed. [7] [8] [9] Must be at least 1.3 V S 0. Must be at least V MC for reciprocating-engine aircraft, or 1.05 V MC for ...
Lift and drag are the two components of the total aerodynamic force acting on an aerofoil or aircraft. In aerodynamics , the lift-to-drag ratio (or L/D ratio ) is the lift generated by an aerodynamic body such as an aerofoil or aircraft, divided by the aerodynamic drag caused by moving through air.