Inaeronautics, atrapezoidal wing is a straight-edged and taperedwing planform. It may have anyaspect ratio and may or may not beswept.[1][2][3]
The thin, unswept, short-span, low-aspect-ratio trapezoidal configuration offers some advantages for high-speed flight and has been used on a small number of aircraft types. In thiswing configuration, theleading edge sweeps back and thetrailing edge sweeps forward.[4] It can provide lowaerodynamic drag at high speeds, while maintaining high strength and stiffness. It was used successfully during the early days of supersonic aircraft.
Any wing with straight leading and trailing edges and with differing root and tipchords is atrapezoid, whether or not it is swept.[5]
The areaA of such a trapezoidal wing may be calculated from the spans, root chordcr and tip chordct:
Thewing loadingw is then given by the liftL divided by the area:
In level flight, the amount of lift is equal to the gross weight.
In a straight trapezoidal wing, such as on theBell X-1, the thickest part of the wing along its span, the line of maximum chord, runs straight out sideways from root to tip. The leading edge then sweeps backwards and the trailing edge sweeps forward.[3] In a swept trapezoidal wing, the line of maximum chord is swept at an angle, usually forward. This increases the sweep of the leading edge and decreases the sweep of the trailing edge, and in the extreme case both edges sweep backwards by different amounts.[5] The transition form, where the trailing edge is straight, is equivalent to a croppeddelta planform.
At supersonic speeds a thin, small and highlyloaded wing offers substantially lower drag than other configurations. Low span and an unswept, tapered planform reduce structural stresses, allowing the wing to be made thin. For minimum drag, wing loading can be in excess of 400 kilograms per square metre (82 lb/sq ft).[citation needed]
Early examples provided a solution to the problem of supersonic flight when engine power was limited. They were made so thin that they had to be machined from a thick, solid sheet of metal.[6] Even with this low-drag wing theDouglas X-3 Stiletto was too underpowered to reach its design flight speed of Mach 2, but the design of its simple hexagonal-airfoil wing was developed for various otherX-planes and for Lockheed's widely producedF-104 Starfighter Mach 2.2 high-altitude interceptor.
The small wing of the Starfighter was found to have good gust response at low level, providing a smooth ride at high subsonic speeds. Consequently, the type was adopted for the ground-attack role, notably by the GermanLuftwaffe. However, the high loading of the wing resulted in a high stalling speed with marginal take-off and landing characteristics and a corresponding high level of takeoff and landing accidents.
A variant with a curved airfoil, blunt trailing edge and conventional internal structure was developed for theNorth American X-15 rocket plane.[6]
Lockheed continued to use the basic design on many of its aircraft proposals in the 1950s, including theLockheed CL-400 Suntan and early versions of theirsupersonic transport designs.[citation needed]
