The lifting delta wing was pioneered by Alexander Lippisch in Germany after World War I, using a thick cantilever wing without any tail. His early designs used a very gentle angle so that the wing appeared almost straight. His first tailless delta aircraft flew in 1931, followed by four successively improved designs. None of these designs were easy to handle at low speed and none saw widespread service.
During the 1930s the French designer Nicolas Roland Payen developed a tandem delta configuration with a straight fore wing and steep delta aft wing, but war stopped the flight testing of the Pa-22. He later flew an experimental tailless delta jet, the Pa.49, in 1954 and the tailless pusher-configuration Arbalète series from 1965.
During World War II Lippisch studied a more advanced tailless delta wing of greater angle intended for high-speed and even supersonic flight, for use in interceptor aircraft. One progressed as far as a glider prototype.
During the postwar period the British developed jet aircraft based on the data from Lippisch, notably the Avro Vulcan strategic bomber and the Gloster Javelin fighter. The Javelin incorporated a tailplane in order to rectify some of the perceived weaknesses of the pure delta, to improve low-speed handling and high-speed manoeuvrability and to allow a greater center of gravity range.
In America Robert T. Jones, working at NACA during World War II, developed the theory of thin delta wings for supersonic flight. First published in January 1945, this approach contrasted with Lippisch's earlier work on thick delta wings. The thin wing provided a successful basis for all practical supersonic deltas.
The tailless delta became a favored design for high-speed aircraft, and was used extensively by Convair and by Dassault Aviation, notably with the Dassault Mirage family and especially the highly successful Mirage III. The F-102 Delta Dagger and Douglas F4D Skyray were two of the first operational jet fighters with a tailless delta wing when they entered service in 1956.
The tailed delta configuration was adopted by the TsAGI (Central Aero and Hydrodynamic Institute, Moscow), to improve high angle-of-attack handling, manoeuvrability and centre of gravity range over a pure delta planform. The MiG-21 ("Fishbed") and Sukhoi Su-9/Su-11/15 fighters were built in large numbers.
Through the 1960s Saab AB developed a close-coupled canard delta configuration, with a delta foreplane just in front of and above the main delta wing. Patented in 1963, it first flew on the Viggen fighter in 1967. The close coupling modifies the airflow over the wing, most significantly when flying at high angles of attack. In contrast to the classic tail-mounted elevators, the canards add to the total lift as well as stabilising the airflow over the main wing. This enables more extreme maneuvers, improves low-speed handling and reduces the takeoff run and landing speed. This configuration has since become common on supersonic fighter aircraft.
Pure delta wings suffer from some undesirable characteristics, notably flow separation at high angles of attack (swept wings have similar problems), and high drag at low speeds. This originally limited them primarily to high-speed, high-altitude interceptor roles. Since then the delta design has been modified in different ways to overcome some of these problems.
Tailed delta – adds a conventional tailplane (with horizontal tail surfaces), to improve handling. Common on Soviet types such as the Mikoyan-Gurevich MiG-21.
Cropped delta – tip is cut off. This helps maintain lift outboard and reduce wingtip flow separation (stalling) at high angles of attack. Most deltas are cropped to at least some degree.
In the compound delta, double delta or cranked arrow, the leading edge is not straight. Typically the inboard section has increased sweepback, creating a controlled high-lift vortex without the need for a foreplane. Examples include the Saab Draken fighter, the prototype F-16XL "Cranked Arrow" and the High Speed Civil Transport study. The ogee delta (or ogival delta) used on the Anglo-French Concorde Mach 2 airliner is similar, but with the two sections and cropped wingtip merged into a smooth ogee curve.
The long root chord and short span of the delta wing make it structurally efficient. It can be built stronger, stiffer and at the same time lighter than a swept wing of equivalent lifting capability. Its long root chord also allows a deeper structure for a given aerofoil section, providing more internal volume for fuel and other storage. Because of its light, robust structure it is easy and relatively inexpensive to build – a substantial factor in the success of the MiG-21 and Mirage aircraft.
The tailless delta wing is not suited to high wing loadings and requires a large wing area for a given aircraft weight. The most efficient aerofoils are unstable in pitch and the tailless type must use a less efficient design and therefore a bigger wing. Techniques used include:
At low speeds a delta wing requires a high angle of attack to maintain lift. A slender delta creates a characteristic vortex pattern over the upper surface which enhances lift. Some types with intermediate sweep have been given retractable "moustaches" or fixed leading-edge root extensions (LERX) to encourage vortex formation.
As the angle of attack increases, the leading edge of the wing generates a vortex which energizes the flow on the upper surface of the wing, delaying flow separation, and giving the delta a very high stall angle. A normal wing built for high speed use typically has undesirable characteristics at low speeds, but in this regime the delta gradually changes over to a mode of lift based on the vortex it generates, a mode where it has smooth and stable flight characteristics.
The vortex lift comes at the cost of increased drag, so more powerful engines are needed to maintain low speed or high angle-of-attack flight.
With a large enough angle of rearward sweep, in the transonic to low supersonic speed range the wing's leading edge remains behind the shock wave boundary or shock cone created by the leading edge root.
This allows air below the leading edge to flow out, up and around it, then back inwards creating a sideways flow pattern. The lift distribution and other aerodynamic characteristics are strongly influenced by this sideways flow.
The rearward sweep angle lowers the airspeed normal to the leading edge of the wing, thereby allowing the aircraft to fly at high subsonic, transonic, or supersonic speed, while the subsonic lifting characteristics of the airflow over the wing are maintained.
Within this flight regime, drooping the leading edge within the shock cone increases lift but not drag. Such conical leading edge droop was introduced on the production Convair F-102A Delta Dagger at the same time that the prototype design was reworked to include area-ruling. It also appeared on Convair's next two deltas, the F-106 Delta Dart and B-58 Hustler.
At high supersonic speeds the shock cone from the leading edge root angles further back to lie along the wing surface behind the leading edge. It is no longer possible for the sideways flow to occur and the aerodynamic characteristics change considerably. It is in this flight regime that the waverider technique, as used on the North American XB-70 Valkyrie, becomes practicable. Here, a shock body beneath the wing creates an attached shockwave and the high pressure associated with the wave provides significant lift without increasing drag.
A lifting-canard delta can offer a smaller shift in the center of lift with increasing Mach number compared to a conventional tail configuration.
An unloaded or free-floating canard can allow a safe recovery from a high angle of attack.
A canard delta foreplane creates its own trailing vortex. If this vortex interferes with the vortex of the main delta wing, this can adversely affect the airflow over the wing and cause unwanted and even dangerous behaviour. In the close-coupled configuration, the canard vortex couples with the main vortex to enhance its benefits and maintain controlled airflow through a wide range of speeds and angles of attack. This allows both improved manoeuvrability and lower stalling speeds, but the presence of the foreplane can increase drag at supersonic speeds and hence reduce the aircraft's maximum speed.
A conventional tail stabiliser allows the main wing to be optimised for lift and therefore to be smaller and more highly loaded.
When used with a T-tail as in the Gloster Javelin, like other wings a delta wing can give rise to a "deep stall" in which the high angle of attack at the stall causes the turbulent wake of the stalled wing to envelope the tail. This makes the elevator ineffective and the airplane cannot recover from the stall.
[Lippisch Delta I and Horten H I] Both these aircraft shown, how not to do it.
|Wikimedia Commons has media related to Delta wings.|
|Look up delta wing in Wiktionary, the free dictionary.|