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This diagram shows lift as perpendicular to the longitudinal body axis. In most technical usage, lift is perpendicular to the oncoming flow. That is, perpendicular to the longitudinal stability axis. At low angles of attack, the lift is generated primarily by the wings, fins and the nose region of the body.
In both cases the lift vector is the same (as seen by an observer on the ground), but in the latter the vertical axis of the aircraft points downwards, making the lift vector's sign negative. In turning flight the load factor is normally greater than +1. For example, in a turn with a 60° angle of bank the load factor is +2. Again, if the same ...
In juxtaposition, the drag reduction felt by trailing agents in formation flight may be thought more of as the trailing agents "surfing" on the vortices shed by wings of leading agents, [4] reducing the amount of force needed to stay in the air. This force is known as lift and acts perpendicular to the freestream flow direction and drag.
They must have a minimum of 240 hours of flying training, the majority of which may be in a full-motion flight simulator with 40 hours and 12 takeoffs and landings total required in an actual airplane before flying passengers (per JAR-FCL 1.120 and 1.125(b)), and 750 hours of classroom theoretical knowledge instruction.
Lift is proportional to the density of the air and approximately proportional to the square of the flow speed. Lift also depends on the size of the wing, being generally proportional to the wing's area projected in the lift direction. In calculations it is convenient to quantify lift in terms of a lift coefficient based on these factors.
This can lead to dramatic improvements in lift for supersonic/hypersonic aircraft. Clarence Syvertson and Alfred J. Eggers discovered this phenomenon in 1956 as they analyzed abnormalities at the reentry of nuclear warheads. [1] The basic concept of compression lift is well known; "planing" boats reduce drag by "surfing" on their own bow wave ...
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The Kutta–Joukowski theorem is a fundamental theorem in aerodynamics used for the calculation of lift of an airfoil (and any two-dimensional body including circular cylinders) translating in a uniform fluid at a constant speed so large that the flow seen in the body-fixed frame is steady and unseparated.