Wing loading, the ratio of an aircraft’s weight to its wing area, affects performance in areas such as lift capacity, landing and takeoff speeds, and maneuverability. Low wing loading values result in better performance at lower speeds, while high-speed aircraft require smaller wing profiles and larger wing-loading figures. Fighter design has led to developments such as combined airframe/wing configurations and variable-sweep wings to maintain low wing loading values while maintaining a small wing profile for supersonic flight.
Wing loading is an aerodynamic variable applied to the aircraft that is a product of the loaded weight of the aircraft divided by its wing area. The wing loading characteristics of any aircraft are design features that dictate overall performance in several areas, including lift capacities, landing and takeoff speeds, and maneuverability. In general, on slower commercial designs, the larger the aircraft’s wings are relative to its weight, the better its overall performance. However, in high-speed designs, the opposite is true, with smaller wings and higher wing loadings giving superior performance. However, some flexibility is necessary in high-speed designs, as they also operate at lower speeds and require multi-purpose wing designs such as variable-sweep and blended-airframe types.
One of the most critical areas of aerodynamic design is the wing load factor of any aircraft. This variable is the cornerstone on which the character of each aircraft design is based. Wing loading is a function of loaded weight and total wing area and is expressed in pounds per square foot (lb/ft2) or kilograms per square meter (kg/m2). To calculate wing loading figures, the total loaded weight of the aircraft is divided by the total area of its wings. The larger the wings are in relation to the total weight of the aircraft, the lower its load factor and vice versa.
This relationship has a fundamental effect on how aircraft engineers achieve their design requirements. For example, aircraft with low wing loading values, that is, those with large wing surfaces in relation to their maximum weight, perform better at lower speeds. They generally have a higher lift capacity with lower takeoff and landing speeds and better performance during climb and cruise phases of flight. They are also more maneuverable throughout their speed range, particularly in the lower gears. However, high-speed aircraft such as fighters generally have smaller wing profiles and larger wing-loading figures, giving them better performance at high speeds.
High-speed fighter jets also have to take off and land, and are often called upon to perform at lower speeds where stability and maneuverability are critical. This wide range of wing loading requirements has led to several side developments in fighter design which included the F-16 and MiG 29 combined airframe/wing configurations and variable-sweep wings on the F-14. This allows for lower wing loading values with its related improvement in low speed performance while maintaining the small wing profile necessary for supersonic flight. The use of leading and trailing edge devices such as Fowler slats and flaps also allows the overall wing area and profile to be tuned for stability and performance during low speed phases of flight. This is an essential feature of wing design in aircraft with large operational speed envelopes, such as large commercial aircraft.
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