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The Cessna 172 Skyhawk is an American four-seat, single-engine, high wing, fixed-wing aircraft made by the Cessna Aircraft Company. [2] First flown in 1955, [2] more 172s have been built than any other aircraft. [3] It was developed from the 1948 Cessna 170 but with tricycle landing gear rather than conventional landing gear.
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.
In fixed-wing aircraft, fuel is usually carried in the wings. While the aircraft is in the air, weight in the wings does not contribute as significantly to the bending moment in the wing as does weight in the fuselage. This is because the lift on the wings and the weight of the fuselage bend the wing tips upwards and the wing roots downwards ...
In fixed-wing aircraft, lateral balance is often much less critical than fore-aft balance, simply because most mass in the aircraft is located very close to its center. An exception is fuel, which may be loaded into the wings, but since fuel loads are usually symmetrical about the axis of the aircraft, lateral balance is not usually affected.
Most importantly, the maximum lift-to-drag ratio is independent of the weight of the aircraft, the area of the wing, or the wing loading. It can be shown that two main drivers of maximum lift-to-drag ratio for a fixed wing aircraft are wingspan and total wetted area. One method for estimating the zero-lift drag coefficient of an aircraft is the ...
The remote control system was tested using a Cessna 172 aircraft over a ten-month period. Boeing choose the Cessna 172 because its approach speed and wing loading were close to that of the YQM-94. At the end of 1971, the YQM-94 remote control system had been tested during 150 flights using eight different remote pilots to control the Cessna 172.
Data from Jane's All The World's Aircraft 1982-83 General characteristics Crew: 1 Capacity: 3 pax Length: 7.24 m (23 ft 9 in) Wingspan: 9.986 m (32 ft 9 in) Height: 2.77 m (9 ft 1 in) Wing area: 13.4 m 2 (144 sq ft) Aspect ratio: 7.45 Airfoil: NACA 63A515 Empty weight: 600 kg (1,323 lb) Max takeoff weight: 990 kg (2,183 lb) Fuel capacity: 162 L (43 US gal; 36 imp gal) fuel ; 7.5 L (2 US gal; 2 ...
The wing is designed so that the angle of incidence is greater at the wing roots and decreases across the span, becoming lowest at the wing tip. This is usually to ensure that at stall speed the wing root stalls before the wing tips , providing the aircraft with continued aileron control and some resistance to spinning .
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