Wave drag is an aerodynamics term that refers to a sudden and very powerful form of drag that appears on aircraft flying at high-subsonic speeds. It is so powerful that it was thought for some time that engines would not be able to provide enough power to easily overcome the effect, which led to the concept of a "sound barrier". However a number of new techniques developed during and just after World War II were able to dramatically reduce the magnitude of the problem, and by the early 1950s most fighter aircraft could reach supersonic speeds without too much trouble. Aerodynamics is a branch of fluid dynamics concerned with the study of gas flows, first analysed by George Cayley in the 1800s. ... For a solid object moving through a fluid or gas, drag is the sum of all the aerodynamic or hydrodynamic forces in the direction of the external fluid flow. ... U.S. Navy F/A-18 at transonic speed. ... World War II was a truly global conflict with many facets: immense human suffering, fierce indoctrinations, and the use of new, extremely devastating weapons like the atom bomb. ... A fighter aircraft is a military aircraft designed primarily for attacking other aircraft, as opposed to a bomber, which is designed to attack ground targets, primarily by dropping bombs. ... This page is about high speed motion of bodies such as airplanes through air or other fluids. ...

Wave drag is caused by the formation of shock waves around the aircraft. Shock waves radiate away a considerable amount of energy, energy that is "seen" by the aircraft as drag. Although shock waves are typically associated with supersonic flow, they can actually form at much lower speeds at areas on the aircraft where the Bernoulli effect accelerates local airflow to supersonic speeds over curved areas. The effect is typically seen at speeds of about Mach 0.8, but it is possible to notice the problem at any speed over that of the critical mach of that aircraft's wing. The magnitude of the rise in drag is impressive, typically peaking at about four times the normal subsonic drag. In fluid dynamics, a shock wave is a nonlinear or discontinuous pressure wave. ... Bernoullis principle states that in fluid flow, an increase in velocity happens simultaneously with decrease in Dutch/Swiss mathematician/scientist Daniel Bernoulli, though it was previously understood by Leonhard Euler and others. ... Mach number (Ma) is defined as a ratio of speed to the speed of sound in the medium in case. ... Critical mach is a aeronautics term that refers to the speed at which some of the airflow on a wing becomes supersonic. ...

If the problem of wave drag is caused by the acceleration of air over curves on the aircraft, the solution is, obviously, to reduce the curves. However this is not always easy, for instance, a wing generates lift at subsonic speeds primarily due to the curvature on the leading edge of the wing. Things are somewhat better for fuselage shaping, but simple things like a cockpit canopy or smoothing off the metal around an air intake can create additional "hot spots". In computing, WinG (pronounced Win Gee) was an API to provide fast graphics performance on Windows 3. ...

When the problem was being studied, wave drag came to be split into two – wave drag caused by the wing as a part of generating lift, and that caused by other portions of the plane. In 1947 studies into both problems led to the development of "perfect" shapes to reduce wave drag as much as theoretically possible. For a fuselage the resulting shape was the Sears-Haack body, which suggested a perfect cross-sectional shape for any given internal volume. The von Kármán ogive was a similar shape for bodies with a blunt end, like a missile. Both were based on long skinny shapes with pointed ends, the main difference being that the ogive was pointy on only one end.

These research projects were quickly put to use by aircraft designers. One common solution to the problem of wave drag due to the wings was to use a swept-wing, which had actually been developed before WWII and used on some German wartime designs (none of which saw service). Sweeping the wing to the rear makes it appear thinner and longer in the direction of the airflow, making a "normal" wing shape closer to that of the von Kármán ogive, while still remaining useful at lower speeds where curvature and thickness are important. The swept wing of an airliner: British Midland Airbus A320-200 A swept-wing is a wing planform used on high-speed aircraft that spend a considerable portion of their flight time in the transonic. ...

One does not have to sweep the wing, it is possible to build a wing that is simply extremely thin. This solution was used on a number of designs, perhaps the most obvious being the F-104 Starfighter. The downside to this approach is that the wing is so thin it is no longer possible to use it for fuel storage or landing gear. The Lockheed F-104 Starfighter was the last of the day fighters, a high-performance supersonic interceptor aircraft capable of high speeds and climb rates. ...

Fuselage shaping was similarly changed with the introduction of the Whitcomb area rule. Whitcomb had been working on testing various airframe shapes for transonic drag when, after watching a presentation by a German researcher in 1952, he realized that the Sears-Haack body had to apply to the entire aircraft. This meant that the fuselage needed to be made considerably skinnier where the wings met it, so that the cross-section of the entire aircraft matched the Sears-Haack body, not just the fuselage itself. The Whitcomb area rule (sometimes just called the area rule) is a design technique used to reduce an aircrafts drag at transonic speeds, speeds between about Mach 0. ...

Several other attempts to reduce wave drag have been introduced over the years, but have not become common. The supercritical airfoil is a new wing design that results in reasonable low speed lift like a normal planform, but has a profile considerably closer to that of the von Kármán ogive. Although the design has been extensively tested, it has not been used, at least in a "pure" form, on any operational designs. An airfoil where the air flow speed at a location on the surface is greater than or equal to the speed of sound. ... In aviation, a planform is the shape and layout of an airplanes wing. ...