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Wing loading is a useful measure of the stalling speed of an aircraft. Wings generate lift owing to the motion of air around the wing. Larger wings move more air, so an aircraft with a large wing area relative to its mass (i.e., low wing loading) will have a lower stalling speed.
The most common high-lift device is the flap, a movable portion of the wing that can be lowered to produce extra lift. When a flap is lowered this re-shapes the wing section to give it more camber. Flaps are usually located on the trailing edge of a wing, while leading edge flaps are used occasionally. There are many kinds of trailing-edge flap.
In the definition of load factor, the lift is not simply that one generated by the aircraft's wing, instead it is the vector sum of the lift generated by the wing, the fuselage and the tailplane, [2]: 395 or in other words it is the component perpendicular to the airflow of the sum of all aerodynamic forces acting on the aircraft.
The wing spar provides the majority of the weight support and dynamic load integrity of cantilever monoplanes, often coupled with the strength of the wing 'D' box itself. . Together, these two structural components collectively provide the wing rigidity needed to enable the aircraft to fly saf
For these airplanes with cantilever wings, the loading case that must be considered when determining the maximum takeoff weight is the airplane with zero fuel and all disposable load in the fuselage. With zero fuel in the wing the only wing bending relief is due to the weight of the wing.
Ball-Bartoe Jetwing used for blown-wing research. Note the "augmentor", intended to direct the discharged airflow over the wingWilliams [8] states some flap blowing tests were done at the Royal Aircraft Establishment before the Second World War, and that extensive tests were done during the war in Germany including flight tests with Arado Ar 232, Dornier Do 24 and Messerschmitt Bf 109 aircraft.
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This means that a safety margin must be used on the main wing area so that its maximum lift coefficient and wing loading are never attained in practice. This in turn means that the main wing must be increased in size. On a three-surface aircraft, the tailplane acts as a conventional horizontal stabiliser. In the stall condition, even if the ...