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141-534: The Gloster Javelin is a twin-engined all-weather interceptor aircraft that served with Britain's Royal Air Force from the mid-1950s until the late 1960s. It was a T-tailed delta-wing aircraft designed for night and all-weather operations and was the last aircraft design to bear the Gloster name. Introduced in 1956 after a lengthy development period, the aircraft received several upgrades during production to its engines, radar and weapons, including support for

282-569: A boxcar . Similarly, their pilots were given less training in combat maneuvers, and more in radio-directed pursuit. The Soviets' main interceptor was initially the Su-9 , which was followed by the Su-15 and the MiG-25 "Foxbat". The auxiliary Tu-128 , an area range interceptor, was notably the heaviest fighter aircraft ever to see service in the world. The latest and most advanced interceptor aircraft in

423-437: A supersonic variant with area-ruled fuselage, thinner wings, and a new tail . The "thin-wing Javelin" would have been capable of about Mach 1.6, with a higher ceiling than contemporary US designs. Initial work started with fitting a thinner-section wing to a Javelin fuselage but as the project developed the changes became so great that it would effectively have been a different aircraft albeit having an outward resemblance to

564-485: A brief period of time they fared rapid development in both speed, range, and altitude. At the end of the 1960s, a nuclear attack became unstoppable with the introduction of ballistic missiles capable of approaching from outside the atmosphere at speeds as high as 3 to 4 miles per second (5 to 7 km/s). The doctrine of mutually assured destruction replaced the trend of defense strengthening, making interceptors less strategically logical. The utility of interceptors waned as

705-462: A chosen aspect of performance. A "point defense interceptor" is of a lightweight design, intended to spend most of its time on the ground located at the defended target, and able to launch on demand, climb to altitude, manoeuvre and then attack the bomber in a very short time, before the bomber can deploy its weapons. At the end of Second World War, the Luftwaffe ' s most critical requirement

846-459: A command centre in the Horse Guards building. The Pup proved to have too low performance to easily intercept Gotha G.IV bombers, and the superior Sopwith Camels supplanted them. The term "interceptor" was in use by 1929. Through the 1930s, bomber aircraft speeds increased so much that conventional interceptor tactics appeared impossible. Visual and acoustic detection from the ground had

987-541: A defensive role since World War I , and are perhaps best known from major actions like the Battle of Britain , when the Supermarine Spitfire and Hawker Hurricane were part of a successful defensive strategy. However, dramatic improvements in both ground-based and airborne radar gave greater flexibility to existing fighters and few later designs were conceived as dedicated day interceptors. Exceptions include

1128-515: A local indentation of the fuselage above and below the wing root. This proved to not be very effective. During the development of the Douglas DC-8 airliner, uncambered airfoils were used in the wing root area to combat the unsweeping. Swept wings on supersonic aircraft usually lie within the cone-shaped shock wave produced at the nose of the aircraft so they will "see" subsonic airflow and work as subsonic wings. The angle needed to lie behind

1269-562: A maximum speed of 525 kn (973 km/h, 605 mph) at this height, be able to perform rapid ascents and attain an altitude of 45,000 feet within ten minutes of engine ignition. Additional criteria given in the requirement included a minimum flight endurance of two hours, a takeoff distance of 1,500 yards, structural strength to support up to 4g manoeuvres at high speed and for the aircraft to incorporate aircraft interception radar , multi-channel VHF radio and various navigational aids. The aircraft would also be required to be economical to produce, at

1410-462: A means of creating positive longitudinal static stability . For a low-speed aircraft, swept wings may be used to resolve problems with the center of gravity , to move the wing spar into a more convenient location, or to improve the sideways view from the pilot's position. By 1905, Dunne had already built a model glider with swept wings followed by the powered Dunne D.5 , and by 1913 he had constructed successful powered variants that were able to cross

1551-472: A much larger area from attack, depending on greater detection capabilities, both in the aircraft themselves and operating with AWACS, rather than high speed to reach targets. The exemplar of this concept was the Tupolev Tu-28 . The later Panavia Tornado ADV was able to achieve long range in a smaller airframe through the use of more efficient engines. Rather than focusing on acceleration and climb rate,

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1692-694: A pair of proposals for interceptor aircraft, the first such designation in the US. One proposal was for a single-engine fighter, the other for a twin-engine. Both were required to reach an altitude of 20,000 feet (6,100 m) in six minutes as a defense against bomber attack. Kelsey said later that he used the interceptor designation to sidestep a hard USAAC policy restricting fighters to 500 pounds (230 kg) of armament. He wished for at least 1,000 pounds (450 kg) of armament so that American fighters could dominate their battles against all opponents, fighters included. The two aircraft resulting from these proposals were

1833-484: A pair of proposed fighter aircraft equipped with swept wings from Hawker Aircraft and Supermarine , the Hawker Hunter and Supermarine Swift respectively, and successfully pressed for orders to be placed 'off the drawing board' in 1950. On 7 September 1953, the sole Hunter Mk 3 (the modified first prototype, WB 188 ) flown by Neville Duke broke the world air speed record for jet-powered aircraft, attaining

1974-567: A pilot attached to Gloster from RAE Farnborough was killed while flying Javelin XA546 having entered what appeared to be an intentional spin. On 8 December 1955, a service test pilot S/L Dick was testing XA561 for the A&;AEE when the aircraft entered a flat spin at 40,000 feet (12,000 m) during manoeuvres testing the buffet boundary, which the anti-spin parachute could not stop, and he chose to eject at 8,000 feet (2,400 m). Following this,

2115-510: A range of only a few miles, which meant that an interceptor would have insufficient time to climb to altitude before the bombers reached their targets. Standing combat air patrols were possible but only at great cost. The conclusion at the time was that " the bomber will always get through ". The invention of radar made possible early, long-range detection of aircraft on the order of 100 miles (160 km), both day and night and in all weather. A typical bomber might take twenty minutes to cross

2256-519: A rate of ten per month for an estimated total of 150 aircraft. Gloster Aircraft developed and produced the only British jet aircraft to be operational during the war, the Gloster Meteor . Through the post-war period, they produced a series of updated versions of the Meteor, including some with delta wing layouts for all or the outer portion of the wings. These were further developed by moving

2397-592: A record-breaking speed of Mach 1.06 (700 miles per hour (1,100 km/h; 610 kn)). The news of a successful straight-wing supersonic aircraft surprised many aeronautical experts on both sides of the Atlantic, as it was increasingly believed that a swept-wing design not only highly beneficial but also necessary to break the sound barrier. During the final years of the Second World War, aircraft designer Sir Geoffrey de Havilland commenced development on

2538-453: A reflex curve at the trailing edge. This results in a much weaker shock wave towards the rear of the upper wing surface and a corresponding increase in critical mach number. Shock waves require energy to form. This energy is taken out of the aircraft, which has to supply extra thrust to make up for this energy loss. Thus the shocks are seen as a form of drag . Since the shocks form when the local air velocity reaches supersonic speeds, there

2679-547: A result, the final 80 FAW 7 aircraft went straight from the factory into storage, eventually flying after being re-manufactured as FAW 9s. A total of 427 Javelins were produced in all variants, plus seven prototypes. While there had been considerable interest from several NATO air forces, there were no export orders for the Javelin. The Javelin was the RAF's first purpose-built all-weather interceptor aircraft. Aerodynamic features of

2820-487: A stall-warning device was developed for the Javelin. By the end of 1956, the Javelin was up to a FAW 7 variant, which was the first to meet the specifications of the original Air Ministry requirement, and which was to become the definitive version of the aircraft (most of which were later altered to the FAW 9 standard). The Javelin was evolving so quickly that deliveries of the FAW 8 began before FAW 7 production had ended. As

2961-619: A step and roughly doubled operational altitudes. Although radars also improved in performance, the gap between offense and defense was dramatically reduced. Large attacks could so confuse the defense's ability to communicate with pilots that the classic method of manual ground controlled interception was increasingly seen as inadequate. In the United States, this led to the introduction of the Semi-Automatic Ground Environment to computerize this task, while in

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3102-478: A strong resemblance to the final Javelin design. The Air Ministry released more detailed specifications on 17 Jun 1949, as F.4/48. Gloster responded with two further updated designs, P.300, which was essentially a quick update to the Meteor with two seats and newer Derwent engines, and the P.316/P.317, another update to the delta layout mounting the Sapphire engines. The P.316 and 317 differed primarily in role, 316

3243-420: A swept wing as it travels through the air. The airflow over a swept wing encounters the wing at an angle. That angle can be broken down into two vectors, one perpendicular to the wing, and one parallel to the wing. The flow parallel to the wing has no effect on it, and since the perpendicular vector is shorter (meaning slower) than the actual airflow, it consequently exerts less pressure on the wing. In other words,

3384-540: A swept wing the wing panels on the Douglas DC-1 outboard of the nacelles also had slight sweepback for similar reasons. 2. to provide longitudinal stability for tailless aircraft, e.g. Messerschmitt Me 163 Kometuu . 3. most commonly to increase Mach-number capability by delaying to a higher speed the effects of compressibility (abrupt changes in the density of the airflow), e.g. combat aircraft, airliners and business jets. Other reasons include: 1. enabling

3525-480: A test flight, the pilot having been distracted by an oxygen supply failure. The official production order for the Javelin was issued in mid-1953; as the Gloster Meteor was still being actively produced by Gloster, considerable elements of the Javelin were subcontracted out to other aviation companies owned by the Hawker Siddeley Group , such as Armstrong Whitworth . While some delays were incurred,

3666-453: A very high fuel consumption. This led fighter prototypes emphasizing acceleration and operational ceiling, with a sacrifice on the loiter time, essentially limiting them to point defense role. Such were the mixed jet/rocket power Republic XF-91 or Saunders Roe SR.53 . The Soviet and Western trials with zero-length launch were also related. None of these found practical use. Designs that depended solely on jet engines achieved more success with

3807-412: A wing carry-through box position to achieve a desired cabin size, e.g. HFB 320 Hansa Jet . 2. providing static aeroelastic relief which reduces bending moments under high g-loadings and may allow a lighter wing structure. For a wing of given span, sweeping it increases the length of the spars running along it from root to tip. This tends to increase weight and reduce stiffness. If the fore-aft chord of

3948-434: A wing is generated by the airflow over it from front to rear. With increasing span-wise flow the boundary layers on the surface of the wing have longer to travel, and so are thicker and more susceptible to transition to turbulence or flow separation, also the effective aspect ratio of the wing is less and so air "leaks" around the wing tips reducing their effectiveness. The spanwise flow on swept wings produces airflow that moves

4089-547: A world speed record. On 12 April 1948, a D.H.108 did set a world's speed record at 973.65 km/h (605 mph), it subsequently became the first jet aircraft to exceed the speed of sound. Around this same timeframe, the Air Ministry introduced a program of experimental aircraft to examine the effects of swept wings, as well as the delta wing configuration. Furthermore, the Royal Air Force (RAF) identified

4230-410: Is a certain " critical mach " speed where sonic flow first appears on the wing. There is a following point called the drag divergence mach number where the effect of the drag from the shocks becomes noticeable. This is normally when the shocks start generating over the wing, which on most aircraft is the largest continually curved surface, and therefore the largest contributor to this effect. Sweeping

4371-507: Is normally used to mean "swept back", but variants include forward sweep , variable sweep wings and oblique wings in which one side sweeps forward and the other back. The delta wing is also aerodynamically a form of swept wing. There are three main reasons for sweeping a wing: 1. to arrange the center of gravity of the aircraft and the aerodynamic center of the wing to coincide more closely for longitudinal balance, e.g. Messerschmitt Me 163 Komet and Messerschmitt Me 262 . Although not

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4512-429: Is placed in an airstream at an angle of yaw – i.e., it is swept back. Now, even if the local speed of the air on the upper surface of the wing becomes supersonic, a shock wave cannot form there because it would have to be a sweptback shock – swept at the same angle as the wing – i.e., it would be an oblique shock. Such an oblique shock cannot form until the velocity component normal to it becomes supersonic." To visualize

4653-447: Is rare and the wing must be unusually rigid. There are two sweep angles of importance, one at the leading edge for supersonic aircraft and the other 25% of the way back from the leading edge for subsonic and transonic aircraft. Leading edge sweep is important because the leading edge has to be behind the mach cone to reduce wave drag. The quarter chord (25%) line is used because subsonic lift due to angle of attack acts there and, up until

4794-446: Is that interceptors often look very impressive on paper, typically outrunning, outclimbing and outgunning slower fighter designs. However, pure interceptors fare poorly in fighter-to-fighter combat against the same "less capable" designs due to limited maneuverability especially at low altitudes and speeds. In the spectrum of various interceptors, one design approach especially shows sacrifices necessary to achieve decisive benefit in

4935-487: The Sabre dance in reference to the number of North American F-100 Super Sabres that crashed on landing as a result. Reducing pitch-up to an acceptable level has been done in different ways such as the addition of a fin known as a wing fence on the upper surface of the wing to redirect the flow to a streamwise direction. The MiG-15 was one example of an aircraft fitted with wing fences. Another closely related design

5076-645: The Convair F-106 Delta Dart , Sukhoi Su-15 , and English Electric Lightning . Through the 1960s and 1970s, the rapid improvements in design led to most air-superiority and multirole fighters , such as the Grumman F-14 Tomcat and McDonnell Douglas F-15 Eagle , having the performance to take on the point defense interception role, and the strategic threat moved from bombers to intercontinental ballistic missiles (ICBMs). Dedicated interceptor designs became increasingly rare, with

5217-635: The De Havilland Firestreak air-to-air missile . The Javelin was succeeded in the interceptor role by the English Electric Lightning , a supersonic aircraft capable of flying at more than double the Javelin's top speed, which was introduced into the RAF only a few years later. The Javelin served for much of its life alongside the Lightning; the last Javelins were withdrawn from operational service in 1968 following

5358-711: The English Channel . The Dunne D.5 was exceptionally aerodynamically stable for the time, and the D.8 was sold to the Royal Flying Corps ; it was also manufactured under licence by Starling Burgess to the United States Navy amongst other customers. Dunne's work ceased with the onset of war in 1914, but afterwards the idea was taken up by G. T. R. Hill in England who designed a series of gliders and aircraft to Dunne's guidelines, notably

5499-522: The F-104 Starfighter (initial A version) and the English Electric Lightning . The role of crewed point defense designs was reassigned to uncrewed interceptors— surface-to-air missiles (SAMs)—which first reached an adequate level in 1954–1957. SAM advancements ended the concept of massed high-altitude bomber operations, in favor of penetrators (and later cruise missiles ) flying a combination of techniques colloquially known as "flying below

5640-627: The F-86D and F-89 Scorpion . In the late 1940s ADC started a project to build a much more advanced interceptor under the 1954 interceptor effort, which eventually delivered the F-106 Delta Dart after a lengthy development process. Further replacements were studied, notably the NR-349 proposal during the 1960s, but came to nothing as the USSR strengthened their strategic force with ICBMs. Hence,

5781-531: The Gloster GA.5 , designed by Richard Walker , and the de Havilland DH.110 , the latter of which held the advantage of also being under consideration for the Royal Navy . Development was considerably delayed through political cost-cutting measures, the number of prototypes being trimmed down to an unworkable level of two each before the decision was entirely reversed; this led to the unusual situation where

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5922-461: The Junkers Ju 287 or HFB 320 Hansa Jet . However, larger sweep suitable for high-speed aircraft, like fighters, was generally impossible until the introduction of fly by wire systems that could react quickly enough to damp out these instabilities. The Grumman X-29 was an experimental technology demonstration project designed to test the forward swept wing for enhanced maneuverability during

6063-554: The Messerschmitt Me 163 Komet , which was the only rocket-powered, crewed military aircraft to see combat. To a lesser degree, the Mikoyan-Gurevich MiG-15 , which had heavy armament specifically intended for anti-bomber missions, was also a specialized day interceptor. Night fighters and bomber destroyers are interceptors of the heavy type, although initially they were rarely referred to as such. In

6204-590: The Westland-Hill Pterodactyl series. However, Dunne's theories met with little acceptance amongst the leading aircraft designers and aviation companies at the time. The idea of using swept wings to reduce high-speed drag was developed in Germany in the 1930s. At a Volta Conference meeting in 1935 in Italy, Adolf Busemann suggested the use of swept wings for supersonic flight. He noted that

6345-418: The de Havilland Comet , which would become the world's first jet airliner. An early design consideration was whether to apply the new swept-wing configuration. Thus, an experimental aircraft to explore the technology, the de Havilland DH 108 , was developed by the firm in 1944, headed by project engineer John Carver Meadows Frost with a team of 8–10 draughtsmen and engineers. The DH 108 primarily consisted of

6486-412: The 1930s and 1940s, but the breakthrough mathematical definition of sweep theory is generally credited to NACA 's Robert T. Jones in 1945. Sweep theory builds on other wing lift theories. Lifting line theory describes lift generated by a straight wing (a wing in which the leading edge is perpendicular to the airflow). Weissinger theory describes the distribution of lift for a swept wing, but does not have

6627-405: The 1980s. The Sukhoi Su-47 Berkut is another notable demonstrator aircraft implementing this technology to achieve high levels of agility. To date, no highly swept-forward design has entered production. The first successful aeroplanes adhered to the basic design of rectangular wings at right angles to the body of the machine. Such a layout is inherently unstable; if the weight distribution of

6768-476: The F-106 ended up serving as the primary USAF interceptor into the 1980s. As the F-106 was retired, intercept missions were assigned to the contemporary F-15 and F-16 fighters, among their other roles. The F-16, however, was originally designed for air superiority while evolving into a versatile multirole fighter. The F-15, with its Mach 2.5 maximum speed enabling it to intercept the fastest enemy aircraft (namely

6909-423: The Javelin remained controllable by using both the trimming capability of the large tailplane and thrust changes to control pitch. Changes from the prototypes included alterations to the rear fuselage and a central "pen nib" fairing extending beyond the engine nozzles, to eliminate buffeting of the rudder by the jet exhaust and increased sweepback of the wing's leading edge to improve high-speed handling. The Javelin

7050-569: The Javelin's status as a "super priority" for production helped to minimize the time involved in producing each aircraft. On 22 July 1954, XA544, the first production aircraft, took flight at Hucclecote . Production was assisted by a large order placed by the United States Air Force , purchasing aircraft for the RAF as part of the Mutual Defense Aid Program at a price of £36.8 million. On 21 October 1954,

7191-529: The Javelin. The third prototype ( WT827 ), and the first to be fitted with operational equipment including radar, first flew on 7 March 1953. The fourth prototype ( WT830) was passed to the Aeroplane and Armament Experimental Establishment (A&AEE) for trials and the fifth prototype, WT836 , made its first flight in July 1954. On 4 July 1954, a prototype Javelin accidentally achieved supersonic speed during

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7332-551: The Javelin. The Gloster P.370 to F.153D for "Thin Wing Gloster All Weather Fighter, an update of the initial F.118 specification was ordered in 1954; a prototype XG336 along with two pre-production aircraft. The final incarnation of the thin-wing Gloster (P.376) just before cancellation was a large aircraft carrying two Red Dean all-aspect missiles as a possible contender for Operational Requirement F.155 . The aircraft, then under construction, and

7473-750: The McDonnell Douglas F-4 Phantom as its primary interceptor from the mid-1970s, with the air defence variant (ADV) of the Panavia Tornado being introduced in the 1980s. The Tornado was eventually replaced with a multirole design, the Eurofighter Typhoon . The Shenyang J-8 is a high-speed, high-altitude Chinese-built single-seat interceptor. Initially designed in the early 1960s to counter US-built B-58 Hustler bombers, F-105 Thunderchief fighter-bombers and Lockheed U-2 reconnaissance planes, it still retains

7614-669: The MiG-25 Foxbat), is also not a pure interceptor as it has exceptional agility for dogfighting based upon the lessons learned from Vietnam; the F-15E Strike Eagle variant adds air interdiction while retaining the interception and air-to-air combat of other F-15s. Presently, the F-22 is the USA's latest combat aircraft that serves in part as an interceptor due to its Mach 2+ speed as well as supercruise capabilities, however it

7755-673: The Soviet (now Russian) inventory is the MiG-31 "Foxhound". Improving on some of the flaws on the proceeding MiG-25, the MiG-31 has better low altitude and low speed performance, in addition to carrying an internal cannon. Russia, despite merging the PVO into the VVS, continues to maintain its dedicated MiG-31 interceptor fleet. In 1937, USAAC lieutenants Gordon P. Saville and Benjamin S. Kelsey devised

7896-462: The UK it led to enormously powerful radars to improve detection time. The introduction of the first useful surface to air missiles in the 1950s obviated the need for fast reaction time interceptors as the missile could launch almost instantly. Air forces increasingly turned to much larger interceptor designs, with enough fuel for longer endurance, leaving the point-defense role to the missiles. This led to

8037-599: The abandonment of a number of short-range designs like the Avro Arrow and Convair F-102 in favor of much larger and longer-ranged designs like the North American F-108 and MiG-25 . In the 1950s and 1960’s during the Cold War , a strong interceptor force was crucial for the opposing superpowers as it was the best means to defend against an unexpected nuclear attack by strategic bombers . Hence, for

8178-470: The ability to 'sprint' at Mach 2+ speeds, and later versions can carry medium-range PL-12/SD-10 MRAAM missiles for interception purposes. The PLAAF/PLANAF currently still operates approximately 300 or so J-8s of various configurations. Several other countries also introduced interceptor designs, although in the 1950s–1960s several planned interceptors never came to fruition, with the expectation that missiles would replace bombers. The Argentine FMA I.Ae. 37

8319-707: The actual aircraft speed is, this becomes a problem during slow-flight phases, such as takeoff and landing. There have been various ways of addressing the problem, including the variable-incidence wing design on the Vought F-8 Crusader , and swing wings on aircraft such as the F-14 , F-111 , and the Panavia Tornado . The term "swept wing" is normally used to mean "swept back", but other swept variants include forward sweep , variable sweep wings and oblique wings in which one side sweeps forward and

8460-493: The aerodynamic properties of the new swept and delta wings, as well as use of the new Armstrong Siddeley Sapphire turbojet engine. On 13 April 1949, the Ministry of Supply issued instructions to two aircraft manufacturers, Gloster and de Havilland , to each construct four airworthy prototypes of their competing designs to meet the requirement, as well as one airframe each for structural testing. These prototype aircraft were

8601-434: The air does have time to react, and is pushed spanwise by the angled leading edge, towards the wing tip. At the wing root, by the fuselage, this has little noticeable effect, but as one moves towards the wingtip the airflow is pushed spanwise not only by the leading edge, but the spanwise moving air beside it. At the tip the airflow is moving along the wing instead of over it, a problem known as spanwise flow . The lift from

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8742-421: The air would be added to the previously perpendicular airflow, resulting in an airflow over the wing at an angle to the leading edge. This angle results in airflow traveling a greater distance from leading edge to trailing edge, and thus the air pressure is distributed over a greater distance (and consequently lessened at any particular point on the surface). This scenario is identical to the airflow experienced by

8883-414: The aircraft changes even slightly, the wing will want to rotate so its front moves up (weight moving rearward) or down (forward) and this rotation will change the development of lift and cause it to move further in that direction. To make an aircraft stable, the normal solution is to place the weight at one end and offset this with an opposite downward force at the other - this leads to the classic layout with

9024-458: The aircraft themselves. They were first to introduce all-weather avionics , assuring successful operations during night, rain, snow, or fog. Countries that were strategically dependent on surface fleet, most notably US and UK, maintained also fleet defense fighters , such as the F-14 Tomcat . During the Cold War , an entire military service, not just an arm of the pre-existing air force,

9165-422: The aircraft to reach speeds closer to Mach 1. One limiting factor in swept wing design is the so-called "middle effect". If a swept wing is continuous - an oblique swept wing - the pressure isobars will be swept at a continuous angle from tip to tip. However, if the left and right halves are swept back equally, as is common practice, the pressure isobars on the left wing in theory will meet the pressure isobars of

9306-438: The aircraft's unorthodox aerodynamic features, the Javelin had a fairly conventional structure and materials, being mainly composed of an aluminium alloy, with some use of steel edging. The fuselage was composed of four sections, the nose (containing the radar radome), the front fuselage, centre fuselage and rear fuselage; the nose and rear fuselage were removable for servicing and easy replacement. The engines were on either side of

9447-434: The aircraft, but too late (at about 400 ft (120 m)), and was killed. The Javelin had experienced a " deep stall "; the wing acting like an airbrake had killed forward motion and at the same time degraded the airflow over the elevators, leaving them useless. Without elevator control, Lawrence was unable to regain control and the aircraft dropped from the sky. A stall warning device was later developed and implemented for

9588-418: The airspeed over the wing was dominated by the normal component of the airflow, not the freestream velocity, so by setting the wing at an angle the forward velocity at which the shock waves would form would be higher (the same had been noted by Max Munk in 1924, although not in the context of high-speed flight). Albert Betz immediately suggested the same effect would be equally useful in the transonic. After

9729-413: The angle of attack at the tip, thus reducing the bending moment on the wing, as well as somewhat reducing the chance of tip stall. However, the same effect on forward-swept wings produces a wash-in effect that increases the angle of attack promoting tip stall. Small amounts of sweep do not cause serious problems, and had been used on a variety of aircraft to move the spar into a convenient location, as on

9870-401: The basic concept of simple sweep theory, consider a straight, non-swept wing of infinite length, which meets the airflow at a perpendicular angle. The resulting air pressure distribution is equivalent to the length of the wing's chord (the distance from the leading edge to the trailing edge). If we were to begin to slide the wing sideways ( spanwise ), the sideways motion of the wing relative to

10011-697: The bombing raids. Rocket-boosted variants of both of Germany's jet fighters; the Me 262 in its "C" subtype series, all nicknamed "home protector" ( Heimatschützer , in four differing formats) and the planned He 162 E subtype, using one of the same BMW 003R turbojet/rocket "mixed-power" engine as the Me 262C-2b Heimatschützer II , but were never produced in quantity. In the initial stage of Cold War , bombers were expected to attack flying higher and faster, even at transonic speeds. Initial transonic and supersonic fighters had modest internal fuel tanks in their slim fuselages, but

10152-412: The capability to include chordwise pressure distribution. There are other methods that do describe chordwise distributions, but they have other limitations. Jones' sweep theory provides a simple, comprehensive analysis of swept wing performance. An explanation of how the swept wing works was offered by Robert T. Jones : "Assume a wing is a cylinder of uniform airfoil cross-section, chord and thickness and

10293-476: The centre fuselage, the internal space in the centre containing the service bay that housed much of the aircraft's electrical, hydraulic, and avionics subsystems. The engine air intakes were placed on the forward fuselage, running directly from beneath the cockpit rearwards into the delta wing. Electricity was provided by a pair of 6,000 watt, 24-volt generators driven by the auxiliary gearbox; inverters provided AC power for equipment such as some flight instruments and

10434-519: The cone increases with increasing speed, at Mach 1.3 the angle is about 45 degrees, at Mach 2.0 it is 60 degrees. The angle of the Mach cone formed off the body of the aircraft will be at about sin μ = 1/M (μ is the sweep angle of the Mach cone) When a swept wing travels at high speed, the airflow has little time to react and simply flows over the wing almost straight from front to back. At lower speeds

10575-631: The defending fighters. The Me 163 required an airbase, however, which were soon under constant attack. Following the Emergency Fighter Program , the Germans developed even odder designs, such as the Bachem Ba 349 Natter , which launched vertically and thus eliminated the need for an airbase. In general all these initial German designs proved difficult to operate, often becoming death traps for their pilots, and had little effect on

10716-458: The design emphasis is on range and missile carrying capacity, which together translate into combat endurance, look-down/shoot-down radars good enough to detect and track fast moving interdictors against ground clutter , and the capability to provide guidance to air-to-air missiles (AAM) against these targets. High speed and acceleration was put into long-range and medium-range AAMs, and agility into short range dog fighting AAMs, rather than into

10857-464: The detection zone of early radar systems, time enough for interceptor fighters to start up, climb to altitude and engage the bombers. Ground controlled interception required constant contact between the interceptor and the ground until the bombers became visible to the pilots and nationwide networks like the Dowding system were built in the late 1930s to coordinate these efforts. During World War II

10998-540: The early Cold War era the combination of jet -powered bombers and nuclear weapons created air force demand for highly capable interceptors; it is in regards to this period that the term is perhaps most recognized and used. Cold War-era interceptors became increasingly distinct from their air superiority counterparts, with the former often sacrificing range, endurance, and maneuverability for speed, rate of climb , and armament dedicated to attacking large strategic bombers . Examples of classic interceptors of this era include

11139-405: The effectiveness of interceptor aircraft meant that bombers often needed to be escorted by long range fighter aircraft. Many aircraft were able to be fitted with Aircraft interception radar , further facilitating the interception of enemy aircraft. The introduction of jet power increased flight speeds from around 300 miles per hour (500 km/h) to around 600 miles per hour (1,000 km/h) in

11280-412: The effects of compressibility in transonic and supersonic aircraft because of the reduced pressures. This allows the mach number of an aircraft to be higher than that actually experienced by the wing. There is also a negative aspect to sweep theory. The lift produced by a wing is directly related to the speed of the air over the wing. Since the airflow speed experienced by a swept wing is lower than what

11421-460: The engine in front and the control surfaces at the end of a long boom with the wing in the middle. This layout has long been known to be inefficient. The downward force of the control surfaces needs further lift from the wing to offset. The amount of force can be decreased by increasing the length of the boom, but this leads to more skin friction and weight of the boom itself. This problem led to many experiments with different layouts that eliminates

11562-421: The engines to the fuselage and using a complete delta wing layout, leading to a second series of designs that continued in parallel. P.228, drawn up in 1946, was essentially a two-seat Meteor with slightly swept wings. A similar design was also offered to the Royal Navy as the P.231. The later-issued P.234 and P.238 of early 1947 had adopted many of the features that would be distinctive of the Javelin, including

11703-480: The event of a war between the Soviet Union and NATO. With the advent of low flying cruise-missiles and high-altitude AA-missiles the flight profile was changed, but regained the interceptor profile with the final version J 35J. Swept wing A swept wing is a wing angled either backward or occasionally forward from its root rather than perpendicular to the fuselage. Swept wings have been flown since

11844-407: The external fuel lines were detached. However, keeping QRA aircraft at this state of readiness was physically and mentally draining to the pilots and was expensive in terms of fuel. As an alternative, longer-range designs with extended loiter times were considered. These area defense interceptors or area defense fighters were in general larger designs intended to stay on lengthy patrol and protect

11985-554: The fastest aircraft of the era were only approaching 400 km/h (249 mph).The presentation was largely of academic interest, and soon forgotten. Even notable attendees including Theodore von Kármán and Eastman Jacobs did not recall the presentation 10 years later when it was re-introduced to them. Hubert Ludwieg of the High-Speed Aerodynamics Branch at the AVA Göttingen in 1939 conducted

12126-445: The first production Javelin was completed before the prototype order being fulfilled. The first prototype was completed in 1951. An unusual feature of the prototypes was the opaque canopy over the rear cockpit. It had been believed that visibility outside the cockpit was unnecessary and a hindrance to the observer; the only external view available was through 2 small ' portholes '. Following a month of ground testing, on 26 November 1951,

12267-434: The first prototype conducted its first flight at Moreton Valence airfield . Bill Waterton , Gloster's Chief Test Pilot, would later describe the Javelin as being "as easy to fly as an Anson ", although also expressing concern over its inadequate power controls. Disaster nearly struck during one test flight when aerodynamic flutter caused the elevators to detach in mid-flight; despite the lack of control surfaces, Bill Waterton

12408-621: The first wind tunnel tests to investigate Busemann's theory. Two wings, one with no sweep, and one with 45 degrees of sweep were tested at Mach numbers of 0.7 and 0.9 in the 11 x 13 cm wind tunnel. The results of these tests confirmed the drag reduction offered by swept wings at transonic speeds. The results of the tests were communicated to Albert Betz who then passed them on to Willy Messerschmitt in December 1939. The tests were expanded in 1940 to include wings with 15, 30 and -45 degrees of sweep and Mach numbers as high as 1.21. With

12549-442: The freestream conditions around the rest of the aircraft, and as the flow enters an adverse pressure gradient in the aft section of the wing, a discontinuity emerges in the form of a shock wave as the air is forced to rapidly slow and return to ambient pressure. At the point where the density drops, the local speed of sound correspondingly drops and a shock wave can form. This is why in conventional wings, shock waves form first after

12690-617: The fuselage, and added a slight sweep to the leading edge of the wing, producing a somewhat delta wing shape. P.240 also replaced the Rolls-Royce Derwent engines with the Metrovick F.9 , which would later move companies and become the Armstrong Siddeley Sapphire . The all-delta layout of P.238 was also updated as P.241, which used an all-delta horizontal stabilizer in a T-tail arrangement. P.241 bears

12831-756: The immediate post-war era, several nations were conducting research into high speed aircraft. In the United Kingdom, work commenced during 1943 on the Miles M.52 , a high-speed experimental aircraft equipped with a straight wing that was developed in conjunction with Frank Whittle 's Power Jets company, the Royal Aircraft Establishment (RAE) in Farnborough , and the National Physical Laboratory . The M.52

12972-598: The interceptor role until it received upgrades in the 1990s for ground attack. Both the fighter and the Phoenix missile were retired in 2006. The British Royal Air Force operated a supersonic day fighter, the English Electric Lightning , alongside the Gloster Javelin in the subsonic night/all-weather role . Efforts to replace the Javelin with a supersonic design under Operational Requirement F.155 came to naught. The UK operated its own, highly adapted version of

13113-538: The introduction of jets in the later half of the Second World War , the swept wing became increasingly applicable to optimally satisfying aerodynamic needs. The German jet-powered Messerschmitt Me 262 and rocket-powered Messerschmitt Me 163 suffered from compressibility effects that made both aircraft very difficult to control at high speeds. In addition, the speeds put them into the wave drag regime, and anything that could reduce this drag would increase

13254-400: The introduction of successively more capable versions of the Lightning. In the aftermath of the Second World War , Britain identified a threat posed by the jet-powered strategic bomber and atomic weaponry and thus placed a great emphasis on developing aerial supremacy through continuing to advance its fighter technology, even following the end of the conflict. Initial planning was based on

13395-494: The introduction of supercritical sections, the crest was usually close to the quarter chord. Typical sweep angles vary from 0 for a straight-wing aircraft, to 45 degrees or more for fighters and other high-speed designs. Shock waves can form on some parts of an aircraft moving at less than the speed of sound. Low-pressure regions around an aircraft cause the flow to accelerate, and at transonic speeds this local acceleration can exceed Mach 1. Localized supersonic flow must return to

13536-465: The large delta wing and tailplane, and were based on the Rolls-Royce AJ65 engine (better known as Avon). The two differed primarily in role; P.234 was a single-seat day fighter with a V-tail , while P.238 was a two-seat night fighter with a mid-mounted delta tailplane. Development of both concepts continued. P.240 of April 1947 was Meteor-like in form but moved the engines from the wings to

13677-399: The maximum Thickness/Chord and why all airliners designed for cruising in the transonic range (above M0.8) have supercritical wings that are flatter on top, resulting in minimized angular change of flow to upper surface air. The angular change to the air that is normally part of lift generation is decreased and this lift reduction is compensated for by deeper curved lower surfaces accompanied by

13818-413: The missile were cancelled in 1957. Data from Gloster Javelin : Profile Number 179 General characteristics Performance Armament Avionics Aircraft of comparable role, configuration, and era Related lists Interceptor aircraft For daytime operations, conventional light fighters have normally filled the interceptor role. Day interceptors have been used in

13959-420: The need for the downward force. One such wing geometry appeared before World War I , which led to early swept wing designs. In this layout, the wing is swept so that portions lie far in front and in back of the center of gravity (CoG), with the control surfaces behind it. The result is a weight distribution similar to the classic layout, but the offsetting control force is no longer a separate surface but part of

14100-668: The only widely used examples designed after the 1960s being the Panavia Tornado ADV , Mikoyan MiG-25 , Mikoyan MiG-31 , and the Shenyang J-8 . The first interceptor squadrons were formed during World War I to defend London against attacks by Zeppelins and later against fixed-wing long-range bombers . Early units generally used aircraft withdrawn from front-line service, notably the Sopwith Pup . They were told about their target's location before take-off from

14241-433: The other back. The delta wing also incorporates the same advantages as part of its layout. Sweeping a wing forward has approximately the same effect as rearward in terms of drag reduction, but has other advantages in terms of low-speed handling where tip stall problems simply go away. In this case the low-speed air flows towards the fuselage, which acts as a very large wing fence. Additionally, wings are generally larger at

14382-436: The overall mission time, there were few ways to reduce this. During the Cold War in times of heightened tensions, quick reaction alert (QRA) aircraft were kept piloted, fully fueled and armed, with the engines running at idle on the runway ready to take off. The aircraft being kept topped up with fuel via hoses from underground fuel tanks. If a possible intruder was identified, the aircraft would be ready to take off as soon as

14523-421: The pairing of the front fuselage of the de Havilland Vampire to a swept wing and small vertical tail; it was the first British swept wing jet, unofficially known as the "Swallow". It first flew on 15 May 1946, a mere eight months after the project's go-ahead. Company test pilot and son of the builder, Geoffrey de Havilland Jr ., flew the first of three aircraft and found it extremely fast – fast enough to try for

14664-458: The performance of their aircraft, notably the notoriously short flight times measured in minutes. This resulted in a crash program to introduce new swept wing designs, both for fighters as well as bombers . The Blohm & Voss P 215 was designed to take full advantage of the swept wing's aerodynamic properties; however, an order for three prototypes was received only weeks before the war ended and no examples were ever built. The Focke-Wulf Ta 183

14805-504: The pioneer days of aviation. Wing sweep at high speeds was first investigated in Germany as early as 1935 by Albert Betz and Adolph Busemann , finding application just before the end of the Second World War . It has the effect of delaying the shock waves and accompanying aerodynamic drag rise caused by fluid compressibility near the speed of sound , improving performance. Swept wings are therefore almost always used on jet aircraft designed to fly at these speeds. The term "swept wing"

14946-440: The premise that another war was at least ten years away, and development was limited mostly to paper projects. Several events in the late 1940s led to this timeline being moved up. In 1947, the Air Ministry issued a requirement for a high-performance night fighter under specification F.44/46 . It called for a two-seat design that would intercept enemy aircraft at heights of up to at least 40,000 feet. It would also have to reach

15087-402: The presentation the host of the meeting, Arturo Crocco , jokingly sketched "Busemann's airplane of the future" on the back of a menu while they all dined. Crocco's sketch showed a classic 1950s fighter design, with swept wings and tail surfaces, although he also sketched a swept propeller powering it. At the time, however, there was no way to power an aircraft to these sorts of speeds, and even

15228-422: The problem. In addition to pitch-up there are other complications inherent in a swept-wing configuration. For any given length of wing, the actual span from tip-to-tip is shorter than the same wing that is not swept. There is a strong correlation between low-speed drag and aspect ratio , the span compared to chord, so a swept wing always has more drag at lower speeds. In addition, there is extra torque applied by

15369-567: The radar". By flying terrain masking low-altitude nap-of-the-earth flight profiles the effective range, and therefore reaction time, of ground-based radar was limited to at best the radar horizon . In the case of ground radar systems this can be countered by placing radar systems on mountain tops to extend the radar horizon, or through placing high performance radars in interceptors or in AWACS aircraft used to direct point defense interceptors. As capabilities continued to improve – especially through

15510-487: The radar. A total of 435 aircraft were built by Gloster (302 built) and Armstrong-Whitworth (133 built); both companies at that time were part of the Hawker Siddeley group. Several were converted to different marks (sometimes repeatedly). Several variants were proposed and investigated but not produced, including aerial reconnaissance versions, a fighter bomber version with underwing panniers for bombs, and

15651-403: The right wing on the centerline at a large angle. As the isobars cannot meet in such a fashion, they will tend to curve on each side as they near the centerline, so that the isobars cross the centerline at right angles to the centerline. This causes an "unsweeping" of the isobars in the wing root region. To combat this unsweeping, German aerodynamicist Dietrich Küchemann proposed and had tested

15792-404: The role merged with that of the heavy air superiority fighter . The interceptor mission is, by its nature, a difficult one. Consider the desire to protect a single target from attack by long-range bombers. The bombers have the advantage of being able to select the parameters of the mission – attack vector, speed and altitude. This results in an enormous area from which the attack can originate. In

15933-431: The root anyway, which allows them to have better low-speed lift. However, this arrangement also has serious stability problems. The rearmost section of the wing will stall first causing a pitch-up moment pushing the aircraft further into stall similar to a swept back wing design. Thus swept-forward wings are unstable in a fashion similar to the low-speed problems of a conventional swept wing. However unlike swept back wings,

16074-436: The single-engine Bell P-39 Airacobra and the twin-engine Lockheed P-38 Lightning . Both aircraft were successful during World War II in standard fighter roles, not specifically assigned to point defense against bombers. From 1946 to 1980 the United States maintained a dedicated Aerospace Defense Command , consisting primarily of dedicated interceptors. Many post-war designs were of limited performance, including designs like

16215-402: The stagnation point on the leading edge of any individual wing segment further beneath the leading edge, increasing effective angle of attack of wing segments relative to its neighbouring forward segment. The result is that wing segments farther towards the rear operate at increasingly higher angles of attack promoting early stall of those segments. This promotes tip stall on back-swept wings, as

16356-554: The swept wing design used by most modern jet aircraft, as this design performs more effectively at transonic and supersonic speeds. In its advanced form, sweep theory led to the experimental oblique wing concept. Adolf Busemann introduced the concept of the swept wing and presented this in 1935 at the Fifth Volta Conference in Rome. Sweep theory in general was a subject of development and investigation throughout

16497-486: The time it takes for the bombers to cross the distance from first detection to being on their targets, the interceptor must be able to start, take off, climb to altitude, maneuver for attack and then attack the bomber. A dedicated interceptor aircraft sacrifices the capabilities of the air superiority fighter and multirole fighter (i.e., countering enemy fighter aircraft in air combat manoeuvring ), by tuning its performance for either fast climbs or high speeds. The result

16638-411: The tips are most rearward, while delaying tip stall for forward-swept wings, where the tips are forward. With both forward and back-swept wings, the rear of the wing will stall first creating a nose-up moment on the aircraft. If not corrected by the pilot the plane will pitch up, leading to more of the wing stalling and more pitch up in a divergent manner. This uncontrollable instability came to be known as

16779-450: The tips on a forward swept design will stall last, maintaining roll control. Forward-swept wings can also experience dangerous flexing effects compared to aft-swept wings that can negate the tip stall advantage if the wing is not sufficiently stiff. In aft-swept designs, when the airplane maneuvers at high load factor the wing loading and geometry twists the wing in such a way as to create washout (tip twists leading edge down). This reduces

16920-404: The tips to bend upwards in normal flight. Backwards sweep causes the tips to reduce their angle of attack as they bend, reducing their lift and limiting the effect. Forward sweep causes the tips to increase their angle of attack as they bend. This increases their lift causing further bending and hence yet more lift in a cycle which can cause a runaway structural failure. For this reason forward sweep

17061-445: The type included its adoption of the new delta wing and a large tailplane. Fuel and armaments were housed in the delta wing, and the engines and crew in the fuselage. The delta wing and tailplane combination had been deemed necessary by Gloster for effective manoeuvrability at high speed and for the aircraft to be controllable at low landing speeds. In one instance during testing, when both elevators had been torn off by elevator flutter,

17202-420: The widespread introduction of the jet engine and the adoption of high speed, low level flight profiles, the time available between detection and interception dropped. Most advanced point defence interceptors combined with long-range radars were struggling to keep the reaction time down enough to be effective. Fixed times, like the time needed for the pilot to climb into the cockpit, became an increasing portion of

17343-472: The wing also remains the same, the distance between leading and trailing edges reduces, reducing its ability to resist twisting (torsion) forces. A swept wing of given span and chord must therefore be strengthened and will be heavier than the equivalent unswept wing. A swept wing typically angles backward from its root rather than forwards. Because wings are made as light as possible, they tend to flex under load. This aeroelasticity under aerodynamic load causes

17484-448: The wing experiences airflow that is slower - and at lower pressures - than the actual speed of the aircraft. One of the factors that must be taken into account when designing a high-speed wing is compressibility , which is the effect that acts upon a wing as it approaches and passes through the speed of sound . The significant negative effects of compressibility made it a prime issue with aeronautical engineers. Sweep theory helps mitigate

17625-402: The wing has the effect of reducing the curvature of the body as seen from the airflow, by the cosine of the angle of sweep. For instance, a wing with a 45 degree sweep will see a reduction in effective curvature to about 70% of its straight-wing value. This has the effect of increasing the critical Mach by 30%. When applied to large areas of the aircraft, like the wings and empennage , this allows

17766-469: The wing to the fuselage which has to be allowed for when establishing the transfer of wing-box loads to the fuselage. This results from the significant part of the wing lift which lies behind the attachment length where the wing meets the fuselage. Sweep theory is an aeronautical engineering description of the behavior of airflow over a wing when the wing's leading edge encounters the airflow at an oblique angle. The development of sweep theory resulted in

17907-524: The wing, which would have existed anyway. This eliminates the need for separate structure, making the aircraft have less drag and require less total lift for the same level of performance. These layouts inspired several flying wing gliders and some powered aircraft during the interwar years. The first to achieve stability was British designer J. W. Dunne who was obsessed with achieving inherent stability in flight. He successfully employed swept wings in his tailless aircraft (which, crucially, used washout ) as

18048-472: Was a prototype jet fighter developed during the 1950s. It never flew and was cancelled in 1960. The Canadian subsonic Avro Canada CF-100 Canuck served in numbers through 1950s. Its supersonic replacement, the CF-105 Arrow ("Avro Arrow"), was controversially cancelled in 1959. The Swedish Saab 35 Draken was specifically designed for intercepting aircraft passing Swedish airspace at high altitudes in

18189-402: Was a single-seat design lacking radar and mounting up to four 1,000 pounds (450 kg) bombs in containers under the fuselage, while 317 was a two-seat design with radar and some form of heavy armament to be determined. The RAF requirements were subject to some changes, mainly in regards to radar equipment and armaments; Gloster also initiated some changes as further research was conducted into

18330-511: Was able to land the aircraft using tailplane trimming and engine thrust for pitch control. He was awarded the George Medal for his actions to retrieve flight data from the burning aircraft. The second prototype (WD808) received a modified wing in 1953. After initial testing by Waterton, it was passed to another Gloster test pilot, Peter Lawrence for his opinion. On 11 June 1953, the aircraft crashed during testing. Lawrence had ejected from

18471-516: Was another swept wing fighter design, but was also not produced before the war's end. In the post-war era, Kurt Tank developed the Ta 183 into the IAe Pulqui II , but this proved unsuccessful. A prototype test aircraft, the Messerschmitt Me P.1101 , was built to research the tradeoffs of the design and develop general rules about what angle of sweep to use. When it was 80% complete, the P.1101

18612-555: Was captured by US forces and returned to the United States , where two additional copies with US-built engines carried on the research as the Bell X-5 . Germany's wartime experience with the swept wings and its high value for supersonic flight stood in strong contrast to the prevailing views of Allied experts of the era, who commonly espoused their belief in the impossibility of manned vehicles travelling at such speeds. During

18753-544: Was designated for deployment of interceptors. The aircraft of the Soviet Air Defence Forces (PVO-S) differed from those of the Soviet Air Forces (VVS) in that they were by no means small or crudely simple, but huge and refined with large, sophisticated radars; they could not take off from grass, only concrete runways; they could not be disassembled and shipped back to a maintenance center in

18894-584: Was designed primarily as a stealth air superiority fighter. In the 1950s, the United States Navy led an unsuccessful F6D Missileer project. Later it launched the development of a large F-111B fleet air defense fighter, but this project was cancelled too. Finally, the role was assigned to the F-14 Tomcat , carrying AIM-54 Phoenix missiles. Like the USAF's F-15, the USN's F-14 was also designed primarily as an air superiority (fighter-to-fighter combat) and F-14s served

19035-515: Was envisioned to be capable of achieving 1,000 miles per hour (1,600 km/h) in level flight, thus enabling the aircraft to potentially be the first to exceed the speed of sound in the world. In February 1946, the programme was abruptly discontinued for unclear reasons. It has since been widely recognised that the cancellation of the M.52 was a major setback in British progress in the field of supersonic design. Another, more successful, programme

19176-522: Was for interceptors as the Commonwealth and American air forces pounded German targets night and day. As the bombing effort grew, notably in early 1944, the Luftwaffe introduced a rocket-powered design, the Messerschmitt Me 163 Komet , in the very-short-range interceptor role. The engine allowed about 7 minutes of powered flight, but offered such tremendous performance that they could fly right by

19317-438: Was reportedly easy to fly even on one engine. The flight controls were fully power-assisted and production aircraft adopted a hydraulic 'feel' system for the pilot. The Javelin featured an infinitely variable airbrake; the airbrake proved to be extremely responsive and effective, allowing pilots to conduct rapid descents and heavy braking manoeuvres, enabling equally rapid landings to be performed. The turnaround time between sorties

19458-542: Was significantly shorter than with the preceding Gloster Meteor, due to improved ground accessibility and engine ignition sequence. Unlike the Meteor, the Javelin was fitted with ejector seats, at the introduction to service of the type. No other operational fighter of the West even to the present day had a bigger wing, in terms of area, than the Javelin, and in the USSR, only the Tu-128 had a larger (about 10m2) wing. In spite of

19599-606: Was the US's Bell X-1 , which also was equipped with a straight wing. According to Miles Chief Aerodynamicist Dennis Bancroft, the Bell Aircraft company was given access to the drawings and research on the M.52. On 14 October 1947, the Bell X-1 performed the first manned supersonic flight, piloted by Captain Charles "Chuck" Yeager , having been drop launched from the bomb bay of a Boeing B-29 Superfortress and attained

19740-483: Was the addition of a dogtooth notch to the leading edge, used on the Avro Arrow interceptor. Other designs took a more radical approach, including the Republic XF-91 Thunderceptor 's wing that grew wider towards the tip to provide more lift at the tip. The Handley Page Victor was equipped with a crescent wing , with three values of sweep, about 48 degrees near the wing root where the wing

19881-471: Was thickest, a 38 degree transition length and 27 degrees for the remainder to the tip. Modern solutions to the problem no longer require "custom" designs such as these. The addition of leading-edge slats and large compound flaps to the wings has largely resolved the issue. On fighter designs, the addition of leading-edge extensions , which are typically included to achieve a high level of maneuverability, also serve to add lift during landing and reduce

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