In aerodynamics, wing loading is the total mass of an aircraft or flying animal divided by the area of its wing. The stalling speed of an aircraft in straight, level flight is partly determined by its wing loading. An aircraft or animal with a low wing loading has a larger wing area relative to its mass, as compared to one with a high wing loading.
The faster an aircraft flies, the more lift can be produced by each unit of wing area, so a smaller wing can carry the same mass in level flight. Consequently, faster aircraft generally have higher wing loadings than slower aircraft. This increased wing loading also increases takeoff and landing distances. A higher wing loading also decreases maneuverability. The same constraints apply to winged biological organisms.
|bird flight upper critical limit||Animal||25||5.1|
|Ozone Buzz Z3 MS||Paraglider||2010||75–95 kg (165–209 lb)||25.8 m2 (278 sq ft)||2.9–3.7||0.59–0.76|
|Wills Wing Sport 2 155||Hang glider||2004||94.8–139.8 kg (209–308 lb)||14.4 m2 (155 sq ft)||6.6–9.7||1.4–2.0|
|upper limit||Microlift glider||2008||220 kg (490 lb) max.||12.2 m2 (131 sq ft) min.[b]||18||3.7|
|CAA (UK) regulations||microlight wing loading limit||2008 [c]||450 kg (990 lb) max. [d]||18 m2 (190 sq ft) min.[e]||25||5.1|
|Schleicher ASW 22||Glider||1981||850 kg (1,870 lb)||16.7 m2 (180 sq ft)||50.9||10.4|
|Piper Warrior||General aviation||1960||1,055 kg (2,326 lb)||15.14 m2 (163.0 sq ft)||69.7||14.3|
|Beechcraft Baron||General aviation twin-engine||1960||2,313 kg (5,099 lb)||18.5 m2 (199 sq ft)||125||26|
|Supermarine Spitfire||Fighter (WWII)||1938||3,039 kg (6,700 lb)||22.48 m2 (242.0 sq ft)||135||28|
|Beechcraft Airliner||Airliner (commuter)||1968||4,727 kg (10,421 lb)||25.99 m2 (279.8 sq ft)||182||37|
|Learjet 31||Business jet||1990||7,031 kg (15,501 lb)||24.57 m2 (264.5 sq ft)||286||59|
|Mikoyan MiG-23||Fighter (variable-geometry)||1970||17,800 kg (39,200 lb)||34.16–37.35 m2 (367.7–402.0 sq ft)||477–521||98–107|
|Lockheed F-104 Starfighter||Fighter (multi-role)||1958||13,166 kg (29,026 lb)||18.22 m2 (196.1 sq ft)||722.6||148.0|
|General Dynamics F-16||Fighter (multi-role)||1978||19,200 kg (42,300 lb)||27.87 m2 (300.0 sq ft)||688.9||141.1|
|McDonnell Douglas F-15 Eagle||Fighter (air superiority)||1976||30,845 kg (68,002 lb)||56.5 m2 (608 sq ft)||546||112|
|Mikoyan-Gurevich MiG-25||Fighter (Interceptor)||1970||36,720 kg (80,950 lb)||61.4 m2 (661 sq ft)||598||122|
|Lockheed SR-71 Blackbird||Strategic Reconnaissance Aircraft||1966||68,946 kg (152,000 lb)||170 m2 (1,800 sq ft)||406||83|
|Fokker F27||Airliner (turboprop)||1958||19,773 kg (43,592 lb)||70 m2 (750 sq ft)||282||58|
|Fokker F28 Fellowship||Airliner (regional jet)||1969||33,000 kg (73,000 lb)||78.97 m2 (850.0 sq ft)||418||86|
|Boeing 737-300||Airliner (Narrow-body)||1984||62,820 kg (138,490 lb)||91.04 m2 (979.9 sq ft)||690||140|
|Boeing 737-900||Airliner (Narrow-body)||2001||84,139 kg (185,495 lb)||124.6 m2 (1,341 sq ft)||675||138|
|Boeing 767||Airliner (Wide-body)||1982||142,882 kg (315,001 lb)||283.3 m2 (3,049 sq ft)||504||103|
|Concorde||Airliner (supersonic)||1976||187,000 kg (412,000 lb)||358.2 m2 (3,856 sq ft)||522||107|
|Rockwell B-1B Lancer||Bomber (variable-geometry)||1983||148,000 kg (326,000 lb)||181.2 m2 (1,950 sq ft)||818||168|
|Boeing 777||Airliner (wide-body)||1995||247,200 kg (545,000 lb)||427.8 m2 (4,605 sq ft)||578||118|
|Boeing 747||Airliner (wide-body)||1970||333,000 kg (734,000 lb)||511 m2 (5,500 sq ft)||652||134|
|Airbus A380||Airliner (wide-body)||2007||575,000 kg (1,268,000 lb)||845 m2 (9,100 sq ft)||680||140|
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. Therefore, an aircraft with lower wing loading will be able to take off and land at a lower speed (or be able to take off with a greater load). It will also be able to turn at a greater rate.
The lift force L on a wing of area A, traveling at true airspeed v is given by
where ρ is the density of air and CL is the lift coefficient. The lift coefficient is a dimensionless number which depends on the wing cross-sectional profile and the angle of attack. At steady flight, neither climbing nor diving, the lift force and the weight are equal. With L/A = Mg/A =WSg, where M is the aircraft mass, WS = M/A the wing loading (in mass/area units, i.e. lb/ft2 or kg/m2, not force/area) and g the acceleration due to gravity, that equation gives the speed v through
As a consequence, aircraft with the same CL at takeoff under the same atmospheric conditions will have takeoff speeds proportional to . So if an aircraft's wing area is increased by 10% and nothing else is changed, the takeoff speed will fall by about 5%. Likewise, if an aircraft designed to take off at 150 mph grows in weight during development by 40%, its takeoff speed increases to = 177 mph.
Some flyers rely on their muscle power to gain speed for takeoff over land or water. Ground nesting and water birds have to be able to run or paddle at their takeoff speed before they can take off. The same is true for a hang glider pilot, though they may get assistance from a downhill run. For all these, a low WS is critical, whereas passerines and cliff dwelling birds can get airborne with higher wing loadings.
To turn, an aircraft must roll in the direction of the turn, increasing the aircraft's bank angle. Turning flight lowers the wing's lift component against gravity and hence causes a descent. To compensate, the lift force must be increased by increasing the angle of attack by use of up elevator deflection which increases drag. Turning can be described as 'climbing around a circle' (wing lift is diverted to turning the aircraft) so the increase in wing angle of attack creates even more drag. The tighter the turn radius attempted, the more drag induced; this requires that power (thrust) be added to overcome the drag. The maximum rate of turn possible for a given aircraft design is limited by its wing size and available engine power: the maximum turn the aircraft can achieve and hold is its sustained turn performance. As the bank angle increases so does the g-force applied to the aircraft, this having the effect of increasing the wing loading and also the stalling speed. This effect is also experienced during level pitching maneuvers.
As stalling is due to wing loading and maximum lift coefficient at a given altitude and speed, this limits the turning radius due to maximum load factor. At Mach 0.85 and 0.7 lift coefficient, a wing loading of 50 lb/sq ft (240 kg/m2) can reach a structural limit of 7.33 g up to 15,000 feet (4,600 m) and then decreases to 2.3 g at 40,000 feet (12,000 m). With a wing loading of 100 lb/sq ft (490 kg/m2) the load factor is twice smaller and barely reaches 1g at 40,000 feet.
Aircraft with low wing loadings tend to have superior sustained turn performance because they can generate more lift for a given quantity of engine thrust. The immediate bank angle an aircraft can achieve before drag seriously bleeds off airspeed is known as its instantaneous turn performance. An aircraft with a small, highly loaded wing may have superior instantaneous turn performance, but poor sustained turn performance: it reacts quickly to control input, but its ability to sustain a tight turn is limited. A classic example is the F-104 Starfighter, which has a very small wing and high 723 kg/m2 (148 lb/sq ft) wing loading.
At the opposite end of the spectrum was the large Convair B-36: its large wings resulted in a low 269 kg/m2 (55 lb/sq ft) wing loading that could make it sustain tighter turns at high altitude than contemporary jet fighters, while the slightly later Hawker Hunter had a similar wing loading of 344 kg/m2 (70 lb/sq ft). The Boeing 367-80 airliner prototype could be rolled at low altitudes with a wing loading of 387 kg/m2 (79 lb/sq ft) at maximum weight.
Like any body in circular motion, an aircraft that is fast and strong enough to maintain level flight at speed v in a circle of radius R accelerates towards the center at . That acceleration is caused by the inward horizontal component of the lift, , where is the banking angle. Then from Newton's second law,
Solving for R gives
The lower the wing loading, the tighter the turn.
Gliders designed to exploit thermals need a small turning circle in order to stay within the rising air column, and the same is true for soaring birds. Other birds, for example those that catch insects on the wing also need high maneuverability. All need low wing loadings.
Wing loading also affects gust response, the degree to which the aircraft is affected by turbulence and variations in air density. A small wing has less area on which a gust can act, both of which serve to smooth the ride. For high-speed, low-level flight (such as a fast low-level bombing run in an attack aircraft), a small, thin, highly loaded wing is preferable: aircraft with a low wing loading are often subject to a rough, punishing ride in this flight regime. The F-15E Strike Eagle has a wing loading of 650 kilograms per square metre (130 lb/sq ft) (excluding fuselage contributions to the effective area), whereas most delta wing aircraft (such as the Dassault Mirage III, for which WS = 387 kg/m2) tend to have large wings and low wing loadings.
Quantitatively, if a gust produces an upward pressure of G (in N/m2, say) on an aircraft of mass M, the upward acceleration a will, by Newton's second law be given by
decreasing with wing loading.
A further complication with wing loading is that it is difficult to substantially alter the wing area of an existing aircraft design (although modest improvements are possible). As aircraft are developed they are prone to "weight growth"—the addition of equipment and features that substantially increase the operating mass of the aircraft. An aircraft whose wing loading is moderate in its original design may end up with very high wing loading as new equipment is added. Although engines can be replaced or upgraded for additional thrust, the effects on turning and takeoff performance resulting from higher wing loading are not so easily reconciled.
Modern gliders often use water ballast carried in the wings to increase wing loading when soaring conditions are strong. By increasing the wing loading the average speed achieved across country can be increased to take advantage of strong thermals. With a higher wing loading, a given lift-to-drag ratio is achieved at a higher airspeed than with a lower wing loading, and this allows a faster average speed across country. The ballast can be ejected overboard when conditions weaken or prior to landing.
A blended wing-fuselage design such as that found on the General Dynamics F-16 Fighting Falcon or Mikoyan MiG-29 Fulcrum helps to reduce wing loading; in such a design the fuselage generates aerodynamic lift, thus improving wing loading while maintaining high performance.
Aircraft like the Grumman F-14 Tomcat and the Panavia Tornado employ variable-sweep wings. As their wing area varies in flight so does the wing loading (although this is not the only benefit). When the wing is in the forward position takeoff and landing performance is greatly improved.
Like all aircraft flaps, Fowler flaps increase the camber and hence the maximum value of lift coefficient (CLmax) lowering the landing speed. They also increase wing area, decreasing the wing loading, which further lowers the landing speed.
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or a stalling speed at the maximum weight authorised not exceeding 35 knots calibrated speed