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Avro Vulcan
Avro Vulcan Bomber RAF.JPEG
A Vulcan B.2 of the RAF
Role Strategic bomber
National origin United Kingdom
Manufacturer A V Roe & Co (Avro)
Hawker Siddeley Aviation
Designer Roy Chadwick/Stuart Davies
First flight 30 August 1952
Introduction 20 July 1956
Retired March 1984
Status Retired from service
Primary user Royal Air Force
Produced 1956–1965
Number built 136 (including prototypes)
Unit cost
£750,000 (1956)

The Avro Vulcan (officially Hawker Siddeley Vulcan from July 1963) is a jet-powered delta wing strategic bomber, which was operated by the Royal Air Force (RAF) from 1956 until 1984. Aircraft manufacturer A.V. Roe and Company (Avro) designed the Vulcan in response to Specification B.35/46. Of the three V bombers produced, the Vulcan was considered the riskiest option. Several scale aircraft, designated Avro 707, were produced to test and refine the delta wing design principles.

The Vulcan B.1 was first delivered to the RAF in 1956; deliveries of the improved Vulcan B.2 started in 1960. The B.2 featured more powerful engines, a larger wing, an improved electrical system and electronic countermeasures (ECM); many were modified to accept the Blue Steel missile. As a part of the V-force, the Vulcan was the backbone of the United Kingdom’s airborne nuclear deterrent during much of the Cold War. Although the Vulcan was typically armed with nuclear weapons, it was capable of conventional bombing missions, a capability which was used in Operation Black Buck during the Falklands War between the United Kingdom and Argentina in 1982.

The Vulcan had no defensive weaponry, initially relying upon high-speed high-altitude flight to evade interception. Electronic countermeasures were employed by the B.1 (designated B.1A) and B.2 from circa 1960. A change to low-level tactics was made in the mid-1960s. In the mid-1970s nine Vulcans were adapted for maritime radar reconnaissance operations, redesignated as B.2 (MRR). In the final years of service six Vulcans were converted to the K.2 tanker configuration for aerial refuelling. Since retirement by the RAF one example, B.2 XH558, named "The Spirit of Great Britain" has been restored for use in display flights and air shows, whilst two other B.2s, XL426 and XM655, are kept in taxiable condition for ground runs and demonstrations at London Southend Airport and Wellesbourne Mountford Airfield respectively.

Development

Origins

Further information: V bombers
Avro Vulcan
Silhouettes of an early Avro 698 concept and the cancelled .

The origin of the Vulcan and the other V bombers is linked with early British atomic weapon programme and nuclear deterrent policies. Britain's atom bomb programme began with Air Staff Operational Requirement OR.1001 issued in August 1946. This anticipated a government decision in January 1947 to authorise research and development work on atomic weapons, the U.S. Atomic Energy Act of 1946 (McMahon Act) having prohibited exporting atomic knowledge, even to countries that had collaborated on the Manhattan Project. OR.1001 envisaged a weapon not to exceed 24 ft 2 in (7.37 m) in length, 5 ft (1.5 m) in diameter and 10,000 lb (4,500 kg) in weight. The weapon had to be suitable for release from 20,000 ft (6,100 m) to 50,000 ft (15,000 m).

In January 1947, the Ministry of Supply distributed Specification B.35/46 to UK aviation companies to satisfy Air Staff Operational Requirement OR.229 for "a medium range bomber landplane capable of carrying one 10,000 lb (4,500 kg) bomb to a target 1,500 nautical miles (1,700 mi; 2,800 km) from a base which may be anywhere in the world." A cruising speed of 500 knots (580 mph; 930 km/h) at heights between 35,000 ft (11,000 m) and 50,000 ft (15,000 m) was specified. The maximum weight when fully loaded ought not to exceed 100,000 lb (45,000 kg). In addition to a "Special" (i.e., atomic) bomb, the aircraft was to be capable of alternatively carrying a conventional bomb load of 20,000 lb (9,100 kg). The similar OR.230 required a "long range bomber" with a 2,000 nautical miles (2,300 mi; 3,700 km) radius of action with a maximum weight of 200,000 lb (91,000 kg) when fully loaded; this requirement was considered too difficult. A total of six companies would submit technical brochures to this specification, including Avro.

Required to tender by the end of April 1947, work began on receipt of Specification B.35/46 at Avro, led by technical director Roy Chadwick and chief designer Stuart Davies; the type designation was Avro 698. It was obvious to the design team that conventional aircraft could not satisfy the Specification; knowing little about high-speed flight and unable to glean much from the Royal Aircraft Establishment or the US, they investigated German Second World War swept wing research. The team estimated that an otherwise conventional aircraft, with a swept wing of 45°, would have doubled the weight requirement. Realising that swept wings increase longitudinal stability, the team deleted the tail (empennage) and the supporting fuselage, it thus became a swept-back flying wing with only a rudimentary forward fuselage and a fin (vertical stabilizer) at each wingtip. The estimated weight was now only 50% over the requirement; a delta shape resulted from reducing the wingspan and maintaining the wing area by filling in the space between the wingtips, which enabled the specification to be met. Though Dr Alexander Lippisch is generally credited as the pioneer of the delta wing, Chadwick’s team had followed its own logical design process. The initial design submission had four large turbojets stacked in pairs buried in the wing either side of the centreline. Outboard of the engines were two bomb-bays.

In August 1947, Roy Chadwick was killed in the crash of the Avro Tudor 2 prototype and was succeeded by Sir William Farren. Reductions in wing thickness made it impossible to incorporate the split bomb bays and stacked engines, thus the engines were placed side-by-side in pairs either side of a single bomb-bay, the fuselage growing somewhat. The wingtip fins gave way to a single fin on the aircraft's centreline. Rival manufacturer Handley Page received a prototype contract for its crescent-winged HP.80 B.35/46 tender in November 1947. Though considered the best option, contract placement for Avro's design was delayed whilst its technical strength was established. Instructions to proceed with the construction of two Avro 698 prototypes was received in January 1948. As an insurance measure against both radical designs failing, Short Brothers received a contract for the prototype SA.4 to the less-stringent Specification B.14/46; the SA.4, later named Sperrin, was not required. In April 1948, Vickers also received authority to proceed with their Type 660 which, although falling short of the B.35/46 Specification, being of a more conventional design would be available sooner; this plane entered service as the Valiant.

Avro 707 and Avro 710

Avro Vulcan
The prototype Vulcans (VX777 front, VX770 rear) with four Avro 707s at Farnborough in September 1953
Main article: Avro 707

As Avro had no flight experience of the delta wing, the company planned two smaller experimental aircraft based on the 698, the one-third scale model 707 for low-speed handling and the one-half scale model 710 for high-speed handling. Two of each were ordered. However, the 710 was cancelled when it was considered too time-consuming to develop; a high-speed variant of the 707 was designed in its place, the 707A. The first 707, VX784, flew in September 1949 but crashed later that month killing the pilot, Avro test pilot Flt Lt Eric Esler. The second low-speed 707, VX790, built with the still uncompleted 707A’s nose section (containing an ejection seat) and redesignated 707B, flew in September 1950 piloted by Avro test pilot Wg Cdr Roland "Roly" Falk. The high speed 707A, WD480, followed in July 1951.

Due to the delay of the 707 programme, the contribution of the 707B and 707A towards the basic design of the 698 was not considered significant, though it did highlight a need to increase the length of the nosewheel to give a ground incidence of 3.5 degrees, the optimum take-off attitude. The 707B and 707A proved the design's validity and gave confidence in the delta planform. A second 707A, WZ736 and a two-seat 707C, WZ744 were also constructed but they played no part in the 698's development.

Vulcan B.1 and B.2

Prototypes and type certification

More influential than the 707 in the 698's design was wind-tunnel testing performed by the Royal Aircraft Establishment at Farnborough, which indicated the need for a wing redesign to avoid the onset of compressibility drag which would have restricted the maximum speed. Painted gloss white, the 698 prototype VX770 flew for the first time on 30 August 1952 piloted by Roly Falk flying solo. The prototype 698, then fitted with only the first-pilot's ejection seat and a conventional control wheel, was powered by four Rolls-Royce RA.3 Avon engines of 6,500 lbf (29 kN) thrust; there were no wing fuel tanks, temporary tankage was carried in the bomb bay. VX770 made an appearance at the 1952 Society of British Aircraft Constructors' (SBAC) Farnborough Air Show the next month when Falk demonstrated an "almost vertical bank". After its Farnborough appearance, the future name of the Avro 698 was a subject of speculation; Avro had strongly recommended the name Ottawa, in honour of the company's connection with Avro Canada. Weekly magazine Flight suggested Albion after rejecting Avenger, Apollo and Assegai. The Chief of the Air Staff preferred a V-class of bombers, the Air Council announced the following month that the 698 would be called Vulcan after the Roman god of fire and destruction. In January 1953, VX770 was grounded for the installation of wing fuel tanks, Armstrong Siddeley ASSa.6 Sapphire engines of 7,500 lbf (33 kN) thrust and other systems; it flew again in July 1953.

Avro Vulcan
Comparison of Vulcan wing designs.

The second prototype, VX777, flew in September 1953. More representative of production aircraft, it was lengthened to accommodate a longer nose undercarriage leg, featured a visual bomb-aiming blister under the cabin and was fitted with Bristol Olympus 100 engines of 9,750 lbf (43.4 kN) thrust. At Falk’s suggestion, a fighter-style control stick replaced the control wheel. Both prototypes had almost pure delta wings with straight leading edges. During trials in July 1954, VX777 was substantially damaged in a heavy landing at Farnborough. It was repaired and fitted with Olympus 101 engines of 11,000 lbf (49 kN) thrust before resuming trials in October 1955. While exploring the high speed and high altitude flight envelope, mild buffeting and other undesirable flight characteristics were experienced while approaching the speed of sound, including an alarming tendency to enter an uncontrollable dive, unacceptable to the Aeroplane and Armament Experimental Establishment (A&AEE) at Boscombe Down. The solution included the "Phase 2" wing, featuring a kinked and drooped leading edge and vortex generators on the upper surface, first tested on 707A WD480. An auto-mach trimmer introduced a nose-up attitude when at high speeds, the control column had to be pushed rather than pulled to maintain level flight.

Meanwhile, the first production B.1, XA889, had flown in February 1955 with the original wing. In September 1955, Falk, flying the second production B.1 XA890 amazed crowds at the Farnborough Air Show by executing a barrel roll on his second flypast in front of the SBAC president’s tent. After two days flying, he was called in front of service and civil aviation authorities and ordered to refrain from carrying out this "dangerous" manoeuvre. Now fitted with a Phase 2 wing, XA889 was delivered in March 1956 to the A&AEE for trials for the type’s initial Certificate of Airworthiness which it received the following month.

Further developments

The first 15 B.1s were powered by the Olympus 101 of 11,000 lbf (49 kN) thrust. Many of these early examples in a metallic finish remained the property of the Ministry of Supply being retained for trials and development purposes. Those entering RAF service were delivered to No 230 Operational Conversion Unit (OCU), the first in July 1956. Later aircraft, painted in anti-flash white and powered by the Olympus 102 of 12,000 lbf (53 kN) thrust, began to enter squadron service in July 1957. The Olympus 102s were quickly modified to Olympus 104 standard, ultimately rated at 13,500 lbf (60 kN) thrust. As far back as 1952, Bristol Aero Engines had begun development of the BOl.6 (Olympus 6) rated at 16,000 lbf (71 kN) thrust but if fitted to the B.1, this would have re-introduced the buffet requiring further redesign of the wing.

The decision to proceed with the B.2 versions of the Vulcan was made in May 1956. It was anticipated that the first B.2 would be around the 45th aircraft of the 99 then on order. As well as being able to achieve greater heights over targets, it was believed that operational flexibility could be extended by the provision of in-flight refuelling equipment and tanker aircraft. The increasing sophistication of Soviet air defences required the fitting of electronic countermeasure (ECM) equipment and vulnerability could be reduced by the introduction of the Avro Blue Steel stand-off missile, then in development. In order to develop these proposals, the second Vulcan prototype VX777 was rebuilt with the larger and thinner Phase 2C wing, improved flying control surfaces and Olympus 102 engines, first flying in this configuration in August 1957. Plans were in hand to equip all Vulcans from the 16th aircraft onwards with in-flight refuelling receiving equipment. A B.1, XA903, was allocated for Blue Steel development work. Other B.1s were used for the development of the BOl.6 (later Olympus 200), XA891; a new AC electrical system, XA893; and ECM including jammers within a bulged tail-cone and a tail-warning radar, XA895.

Avro Vulcan
The first Avro Vulcan B.2, XH533, flying at Farnborough, 1958.

The 46th production aircraft and first B.2, XH533, first flew in September 1958 fitted with Olympus 200 engines of 16,000 lbf (71 kN) thrust, six months before the last B.1 XH532 was delivered in March 1959. Rebuilding B.1s as B.2s was considered but rejected over cost. Nevertheless, to extend the B.1's service life, 28 were upgraded by Armstrong Whitworth between 1959 and 1963 to the B.1A standard, including features of the B.2 such as ECM equipment, in-flight refuelling receiving equipment, and UHF radio. The second B.2, XH534, flew in January 1959. Powered by production Olympus 201 of 17,000 lbf (76 kN) thrust, it was more representative of a production aircraft, being fitted with an in-flight refuelling probe and a bulged ECM tail cone. Some subsequent B.2s were initially lacking probes and ECM tail cones, but these were fitted retrospectively. The first 10 B.2s outwardly showed their B.1 ancestry, retaining narrow engine air intakes. Anticipating even more powerful engines, the air intakes were deepened on the 11th (XH557) and subsequent aircraft. Many of the early aircraft were retained for trials and it was the 12th B.2, XH558, that was the first to be delivered to the RAF in July 1960.

The 26th B.2, XL317, the first of a production batch ordered in February 1956, was the first Vulcan, apart from development aircraft, capable of carrying the Blue Steel missile; 33 aircraft were delivered to the RAF with these modifications. When the Mk.2 version of Blue Steel was cancelled in favour of the Douglas GAM-87 Skybolt air-launched ballistic missile in December 1959, fittings were changed in anticipation of the new missile, one under each wing. Though Skybolt was cancelled in November 1962, many aircraft were delivered or retrofitted with "Skybolt" blisters. Later aircraft (XL391 and XM574 onwards) were delivered with Olympus 301 engines of 20,000 lbf (89 kN) thrust. Two earlier aircraft were re-engined (XH557 and XJ784) for trials and development work; another seven aircraft (XL384-XL390) were converted circa 1963.

The last B.2 was delivered in 1965 and the type served till 1984. Whilst in service the B.2 was continuously updated with modifications including rapid engine starting, bomb-bay fuel tanks, wing strengthening to give the fatigue life to enable the aircraft to fly at low level (a tactic introduced in the mid-60s), upgraded navigation equipment, Terrain Following Radar (TFR), standardisation on a common nuclear weapon (WE.117) and improved ECM equipment. The B.1As were not strengthened, thus all were withdrawn by 1968. Nine B.2s were modified for the Maritime Radar Reconnaissance (MRR) role and six for the airborne tanker role.

Proposed developments and cancelled projects

Avro Type 718

The Avro 718 was a 1951 proposal for a delta-winged military transport based on the Type 698 to carry 80 troops or 110 passengers. It would have been powered by four Bristol Olympus BOl.3 engines.

Avro Atlantic
Main article: Avro Atlantic

The Avro Type 722 Atlantic was a 1952 proposal (announced in June 1953) for a 120-passenger delta-winged airliner based on the Type 698.

Avro Type 732

The Avro 732 was a 1956 proposal for a supersonic development of the Vulcan and would have been powered by 8 de Havilland Gyron Junior engines. Unlike the proposed Avro 721 low-level bomber of 1952 or the Avro 730 supersonic stainless steel canard bomber dating from 1954 (cancelled in 1957 before completion of the prototype), the Type 732 showed its Vulcan heritage.

Vulcan Phase 6 (Vulcan B.3)
Avro Vulcan
Silhouette of the original study for the Vulcan B.3 Patrol Missile Carrier.

In 1960, the Air Staff approached Avro with a request into a study for a Patrol Missile Carrier armed with up to six Skybolt missiles capable of a mission length of 12 hours. Avro's submission in May 1960 was the Phase 6 Vulcan, which if built would have been the Vulcan B.3. The aircraft was fitted with an enlarged wing of 121 ft (37 m) span with increased fuel capacity; additional fuel tanks in a dorsal spine; a new main undercarriage to carry an all-up-weight of 339,000 lb (154,000 kg); and reheated Olympus 301s of 30,000 lbf (130 kN) thrust. An amended proposal of October 1960 inserted a 10 ft 9 in (3.28 m) plug into the forward fuselage with capacity for six crew members including a relief pilot, all facing forwards on ejection seats, and aft-fan versions of the Olympus 301.

Export proposals

Other countries expressed interest to purchase Vulcans but, as with the other V-bombers, no foreign sales materialised.

Australia

As early as 1954, Australia recognised that the English Electric Canberra was becoming outdated and evaluated aircraft such as the Avro Vulcan and Handley-Page Victor as potential replacements. Political pressure for a Canberra replacement only rose to a head in 1962; at which point more modern types such as the BAC TSR-2, General Dynamics F-111C, and North American A-5 Vigilante had become available. The RAF would have transferred several V-bombers, including Vulcans, for interim use by the RAAF if they had purchased the TSR-2, but the RAAF selected the F-111C.

Argentina

In the early 1980s, Argentina approached the UK with a proposal to buy a number of Vulcans. An application, made in September 1981, requested the 'early availability' of a 'suitable aircraft'. With some reluctance, ministers approved the export of a single aircraft but emphasised that clearance had not been given for the sale of a larger number. A letter from the British Foreign and Commonwealth Office to the Ministry of Defence in January 1982 stated that little prospect was seen of this happening without ascertaining the Argentine interest and whether such interest was genuine: 'On the face of it, a strike aircraft would be entirely suitable for an attack on the Falklands.' Argentina invaded the Falkland Islands less than three months later.

Design

Avro Vulcan
Avro Vulcan XH558 at Duxford Airshow 2012

Overview

In spite of its radical and unusual shape, the airframe was built along traditional lines. Except for the most highly stressed parts, the whole structure was manufactured from standard grades of light alloy. The airframe was broken down into a number of major assemblies: the centre section, a rectangular box containing the bomb-bay and engine bays bounded by the front and rear spars and the wing transport joints; the intakes and centre fuselage; the front fuselage, incorporating the pressure cabin; the nose; the outer wings; the leading edges; the wing trailing edge and tail end of the fuselage; the wings were not sealed and used directly as fuel tankage, but carried bladders for fuel in the void spaces of the wings; and there was a single swept tail fin with a single rudder on the trailing edge.

The normal crew of five, the first pilot, co-pilot, navigator radar, navigator plotter and air electronics officer (AEO) was accommodated within the pressure cabin on two levels, the pilots sitting on Martin-Baker 3K (3KS on the B.2) ejection seats whilst on the lower level, the rest of the crew sat facing rearwards and had to abandon the aircraft through the entrance door. The original B35/46 specification had specified a jettisonable crew compartment but this requirement was removed in a subsequent amendment and the issue of not providing the rear crew with ejection seats remained highly controversial, especially when a practical scheme to fit them was rejected. A rudimentary sixth seat was provided forward of the navigator radar for an additional crew member; the B.2 also had an additional seventh seat on the opposite side from the sixth seat and forward of the AEO. These seats were no more than cushions and a full harness and an oxygen and intercom facility. The visual bomb-aimer’s compartment could be fitted with a T4 (Blue Devil) bombsight but in most B.2s, the space was eventually fitted with a vertically mounted Vinten F95 Mk.10 camera for the assessment of simulated low-level bombing runs.

Fuel was carried in 14 bag tanks, four in the centre fuselage above and to the rear of the nosewheel bay and five in each outer wing. The tanks were split into four groups of almost equal capacity, each normally feeding its respective engine though cross-feeding was possible. The centre of gravity was automatically maintained by electric timers which sequenced the booster pumps on the tanks. B.2 aircraft could be fitted with one or two additional fuel tanks in the bomb-bay.

Despite being designed before a low radar cross-section (RCS) and other stealth factors were ever a consideration, a Royal Aircraft Establishment technical note of 1957 stated that of all the aircraft so far studied, the Vulcan due to its shape appeared by far the simplest radar echoing object: only one or two components contributing significantly to the echo at any aspect, compared with three or more on most other types.

Avionics

The original Vulcan B.1 radio fit was: two 10-channel VHF transmitter/receivers (TR-1985/TR-1986) and a 24-channel HF transmitter/receiver (STR-18). The Vulcan B.1A also featured an UHF transmitter/receiver (ARC-52). The initial B.2 radio fit was similar to the B.1A though it was ultimately fitted with the ARC-52, a V/UHF transmitter/receiver (PTR-175), and a SSB HF transmitter/receiver (Collins 618T).

The Navigation and Bombing System (NBS) comprised an H2S Mk9 radar and a Navigation Bombing Computer (NBC) Mk1. Other B.1 navigation aids included a Marconi radio compass (ADF), GEE Mk3, Green Satin Doppler radar to determine the groundspeed and drift angle, radio and radar altimeters, and ILS. TACAN replaced GEE in the B.1A and B.2 and Decca Doppler 72 replaced Green Satin in the B.2. A continuous display of the aircraft's position was maintained by a Ground Position Indicator (GPI).

Vulcan B.2s were eventually fitted with the twin-gyro free-running gyroscopic Heading Reference System (HRS) Mk.2, based upon the inertial platform of the Blue Steel missile, which had been integrated into the system when the missile had been carried. With the HRS a Navigator's Heading Unit (NHU)was provided which enabled the Navigator Plotter to adjust the aircraft heading, through the autopilot, by as little as 0.1 degrees. The B.2 (MRR) was additionally fitted with the LORAN C navigation system.

The original ECM fit as fitted to the B.1A and B.2 was: one Green Palm voice communications' jammer; two Blue Diver metric jammers; three Red Shrimp S-band jammers; ; a Blue Saga Passive Warning Receiver with 4 aerials (PWR); one Red Steer tail-warning radar; and window (chaff) dispensers. The bulk of the equipment was carried in a large extended tail cone, and a flat ECM aerial counterpoise plate mounted between the starboard tailpipes. Later equipment on the B.2 included: an L-band jammer (replacing a Red Shrimp); the ARI 18146 X-band jammer; replacing the Green Palm; the improved Red Steer Mk.2; infra-red decoys (flares); and the ARI 18228 PWR with its aerials that gave a squared top to the fin.

Colour schemes

Avro Vulcan
Aerial view of a Vulcan B.2 in late RAF markings on static display at RAF Mildenhall

The two prototype Vulcans were finished in gloss white. Early Vulcan B.1s left the factory in a natural metal finish; the front half of the nose radome was painted black, the rear half painted silver. Front-line Vulcan B.1s had a finish of anti-flash white and RAF "type D" roundels. Front-line Vulcan B.1As and B.2s were similar but with 'type D pale' roundels.

With the adoption of low-level attack profiles in the mid-1960s, B.1As and B.2s were given a glossy Sea Grey Medium and Dark Green disruptive pattern camouflage on the upper surfaces, white undersurfaces and "type D" roundels. (The last 13 Vulcan B.2s, XM645 onwards, were delivered thus from the factory). In the mid-1970s: Vulcan B.2s received a similar scheme with matte camouflage, Light Aircraft Grey undersides, and "low-visibility" roundels; B.2(MRR)s received a similar scheme in gloss; and the front half of the radomes were no longer painted black. Beginning in 1979, 10 Vulcans received a wrap-around camouflage of Dark Sea Grey and Dark Green because, during Red Flag exercises in the USA, defending SAM forces had found that the grey-painted undersides of the Vulcan became much more visible against the ground at high angles of bank.

Controls

Avro Vulcan
Vulcan B.1 XA890 in early silver scheme landing at Farnborough in September 1955 after Roly Falk's "aerobatic" display. Note the lower outer starboard airbrake, which was later deleted

The aircraft was controlled by a fighter-type control stick and rudder bar which operated the powered flying controls (PFCs). Each PFC had a single electro-hydraulic powered flying control unit (PFCU) except the rudder which had two, one running as a back-up. Artificial feel and autostabilisation in the form of pitch and yaw dampers were provided, as well as an auto mach trimmer.

The flight instruments in the B.1 were traditional and included G4B compasses; Mk.4 artificial horizons; and zero reader flight display instruments. The B.1 had a Smiths Mk10 autopilot. In the B.2, these features were incorporated into the Smiths Military Flight System (MFS), the pilots' components being: two beam compasses; two director-horizons; and a Mk.10A or Mk.10B autopilot. From 1966, B.2s were fitted with the ARI 5959 Terrain-following radar (TFR), built by General Dynamics, its commands being fed into the director-horizons.

The B.1 had four elevators (inboard) and four ailerons (outboard). In the B.2, these were replaced by eight elevons. The Vulcan was also fitted with six electrically-operated three-position (in, medium drag, high drag) airbrakes, four in the upper centre section and two in the lower. There were originally four lower airbrakes but the outboard two were deleted before the aircraft entered service. A brake parachute was installed inside the tail cone.

Electrical and hydraulic systems

The main electrical system on the B.1/B.1A was 112V DC supplied by four 22.5kW engine-driven generators. Backup power was provided by four 24V 40Ah batteries connected in series providing 96V. Secondary electrical systems were 28V DC, single-phase 115V AC at 1600Hz, and three-phase 115V AC at 400 Hz, driven by transformers and inverters from the main system. The 28V DC system was backed up by a single 24V battery.

For greater efficiency and higher reliability, the main system on the B.2 was changed to three-phase 200V AC at 400 Hz supplied by four 40kVA engine-driven constant speed alternators. Standby supplies in the event of a main AC failure were provided by a Ram Air Turbine (RAT) driving a 17kVA alternator that could operate at high altitude down to 20,000 ft (6,100 m), and an Airborne Auxiliary Power Plant (AAPP), a Rover gas turbine driving a 40kVA alternator, which could be started once the aircraft was below an altitude of 30,000 ft (9,100 m). Secondary electrical supplies were similar to the B.1.

The change to an AC system was a significant improvement. The Vulcan's powered flying controls were hydraulically actuated but each Powered Flying Control Unit (PFCU) had a hydraulic pump which was driven by an electrical motor. Because there was no manual reversion, a total electrical failure would result in a loss of control. The standby batteries on the B.1 were designed to give enough power for 20 minutes of flying time but this proved to be optimistic and two aircraft, XA891 and XA908, crashed as a result.

The main hydraulic system provided pressure for: undercarriage raising and lowering and bogie trim; nosewheel centring and steering; wheelbrakes (fitted with Maxarets); bomb doors opening and closing; and (B.2 only) AAPP air scoop lowering. Hydraulic pressure was provided by three hydraulic pumps fitted to Nos. 1, 2 and 3 engines. An electrically operated hydraulic power pack (EHPP) could be used to operate the bomb doors and recharge the brake accumulators. A compressed air (later nitrogen) system was provided for emergency undercarriage lowering.

Engine

Main article: Rolls-Royce Olympus

The Rolls-Royce Olympus, originally known as the "Bristol BE.10 Olympus", is a two-spool axial-flow turbojet that powered the Vulcan. Each Vulcan had four engines buried in the wings, positioned in pairs close to the centre of the fuselage. The engine's design began in 1947, intended to power the Bristol Aeroplane Company's own rival design to the Vulcan. A serendipitous arrangement in air intakes can cause the Vulcan to emit a distinctive "howl" when the engines are at approximately 90% power, which can be heard as the aircraft performs a flypast, such as at public airshows.

Avro Vulcan
Gas-flow diagram of an Olympus Mk 101 engine

As the prototype Vulcan VX770 was ready for flight prior to the Olympus being available, it first flew using Rolls-Royce Avon RA.3 engines of 6,500 lbf (29 kN) thrust. These were quickly replaced by Armstrong Siddeley Sapphire ASSa.6 engines of 7,500 lbf (33 kN) thrust. VX770 later became a flying test bed for the Rolls-Royce Conway. The second prototype VX777 first flew with Olympus 100s of 10,000 lbf (44 kN) thrust. It was subsequently re-engined with Olympus 101 engines of 11,000 lbf (49 kN) thrust. When VX777 flew with a Phase 2C (B.2) wing in 1957, it was fitted with Olympus 102 engines of 12,000 lbf (53 kN) thrust.

Early B.1s were engined with the Olympus 101. Later aircraft were delivered with Olympus 102s. All Olympus 102s became the Olympus 104 of 13,000 lbf (58 kN) thrust on overhaul and ultimately 13,500 lbf (60 kN) thrust on uprating. The first B.2 flew with the second-generation Olympus 200 of 16,000 lbf (71 kN) thrust, design of which began in 1952. Subsequent B.2s were engined with either the uprated Olympus 201 of 17,000 lbf (76 kN) thrust or the Olympus 301 of 20,000 lbf (89 kN) thrust. The Olympus 201 was designated 202 on being fitted with a rapid air starter. The engine would later be developed into a reheated (afterburning) powerplant for the cancelled supersonic BAC TSR-2 strike bomber and the supersonic passenger transport Concorde.

Operational history

Introduction

In September 1956, the RAF received its first Vulcan B.1, XA897, which immediately embarked upon a round-the-world tour. The tour was to be an important demonstration of the range and capabilities of the aircraft, it also had other benefits in the form of conducting goodwill visits in various countries; in later life Vulcans routinely visited various nations and distant parts of the former British Empire as a show of support and military protection. This first tour, however, was struck by misfortune; on 1 October 1956, while landing in bad weather at London Heathrow Airport at the completion of the world tour, XA897 was destroyed in a .

Avro Vulcan
A Vulcan B1A of the Waddington Wing at Filton during a public air display in the 1960s

The first two aircraft were delivered to 230 OCU in January 1957 and the training of crews started on 21 February 1957, in the following months more aircraft were delivered to the OCU. The first OCU course to qualify was No. 1 Course, on 21 May 1957, and they went on to form the first flight of No.83 Squadron. No. 83 Squadron was the first operational squadron to use the bomber, at first using borrowed Vulcans from the OCU and on 11 July 1956 it received the first aircraft of its own. By September 1957, several Vulcans had been handed over to No.83 Squadron The second OCU course also formed a Flight of 83 Squadron, but subsequent trained crews were also used to form the second bomber squadron, 101 Squadron. The last aircraft from the first batch of 25 aircraft had been delivered by the end of 1957 to 101 Squadron.

In order to increase the mission range and flight time for Vulcan operations, in-flight refuelling capabilities were added in 1959 onwards; several Valiant bombers were refurbished as tankers to refuel the Vulcans. Continuous airborne patrols proved untenable, however, and the refuelling mechanisms across the Vulcan fleet fell into disuse in the 1960s. Both Vulcans and the other V-force aircraft routinely visited the Far East, in particular Singapore, where a fully equipped nuclear weapons storage facility had been constructed in 1959. During the Indonesia–Malaysia confrontation Britain planned to deploy three squadrons of V-bomber aircraft and 48 Red Beard tactical nuclear weapons to the region, although this was ultimately decided against, Vulcans trained in the region for both conventional and nuclear missions. Britain regularly deployed of Vulcans to the Far East as a part of their contribution to SEATO operations, often to test the defenses of friendly nations in joint exercises. In the early 1970s, the RAF decided to permanently deploy two squadrons of Vulcans overseas in the Near East Air Force Bomber Wing, based at RAF Akrotiri in Cyprus; the Vulcans were withdrawn as Cypriot intercommunal violence intensified in the mid-1970s.

Avro Vulcan
Royal Air Force Vulcan B.2 being prepared for flight on 25 May 1985

Vulcans did some very long range missions. In June 1961, one of them took off from RAF Scampton to Sydney, with an 18,507 km long journey, flown in only a bit more than 20 hours and three air refuellings. Vulcans frequently visited the United States during the 1960s and 1970s to participate in air shows and static displays, as well as to participate in the Strategic Air Command's Annual Bombing and Navigation Competition at such locations as Barksdale AFB, Louisiana and the former McCoy AFB, Florida, with the RAF crews representing Bomber Command and later Strike Command. Vulcans also took part in the 1960, 1961, and 1962 Operation Skyshield exercises, in which NORAD defences were tested against possible Soviet air attack, the Vulcans simulating Soviet fighter/bomber attacks against New York, Chicago and Washington. The results of the tests were classified until 1997. Another successful use of the Vulcan happened with the 'Giant Voice' exercise, 1974. Even then, when Vulcan was quite obsolescent, RAF bombers managed to avoid USAF interceptors

Nuclear deterrent

As part of Britain's independent nuclear deterrent, the Vulcan initially carried Britain's first nuclear weapon, the Blue Danube gravity bomb. Blue Danube was a low-kiloton yield fission bomb designed before the United States detonated the first hydrogen bomb. These were supplemented by U.S.-owned Mk 5 bombs (made available under the Project E programme) and later by the British Red Beard tactical nuclear weapon. The UK had previously embarked on its own hydrogen bomb programme, and to bridge the gap until these were ready the V-bombers were equipped with an Interim Megaton Weapon based on the Blue Danube casing containing Green Grass, a large pure-fission warhead of 400 kt (1.7 PJ) yield. This bomb was known as Violet Club. Only five were deployed before the Green Grass warhead was incorporated into a developed weapon as Yellow Sun Mk.1.

The later Yellow Sun Mk 2, was fitted with Red Snow, a British-built variant of the U.S. W28 warhead. Yellow Sun Mk 2 was the first British thermonuclear weapon to be deployed, and was carried on both the Vulcan and Handley Page Victor. The Valiant retained U.S. nuclear weapons assigned to SACEUR under the dual-key arrangements. Red Beard was pre-positioned in Singapore for use by Vulcan and Victor bombers. From 1962, three squadrons of Vulcan B.2s and two squadrons of Victor B.2s were armed with the Blue Steel missile, a rocket-powered stand-off bomb, which was also armed with the 1.1 Mt (4.6 PJ) yield Red Snow warhead.

Operationally, RAF Bomber Command and the U.S. Strategic Air Command cooperated in the Single Integrated Operational Plan (SIOP) to ensure coverage of all major Soviet targets from 1958, 108 aircraft of the RAF's V-Bombers were assigned targets under SIOP by the end of 1959. From 1962 onwards, two jets in every major RAF base were armed with nuclear weapons and on standby permanently under the principle of Quick Reaction Alert (QRA). Vulcans on QRA standby were to be airborne within four minutes of receiving an alert, as this was identified as the amount of time between warning of a USSR nuclear strike being launched and it arriving in Britain. The closest the Vulcan came to take part in potential nuclear conflict was during the Cuban missile crisis in October 1962, where Bomber Command was moved to Alert Condition 3, an increased state of preparedness from normal operations, however stood down in early November.

Avro Vulcan
XH558 taking off; 2008 Farnborough Airshow

The Vulcans were intended to be equipped with the American Skybolt Air Launched Ballistic Missile to replace the Blue Steel, with Vulcan B.2s carrying two Skybolts under the wings; the last 28 B.2s were modified on the production line to fit pylons to carry the Skybolt. A with increased wingspan to carry up to six Skybolts was proposed in 1960. When the Skybolt missile system was cancelled by U.S. President John F. Kennedy on the recommendation of his Secretary of Defense, Robert McNamara in 1962, Blue Steel was retained. To supplement it until the Royal Navy took on the deterrent role with Polaris ICBM-equipped submarines, the Vulcan bombers adopted a new mission profile of flying high during clear transit, dropping down low to avoid enemy defences on approach, and deploying a parachute-retarded bomb, the WE.177B. However, since the aircraft had been designed for high-altitude flight, at low altitudes it could not exceed 350 knots. RAF Air Vice Marshal Ron Dick, a former Vulcan pilot, said "it is [thus] questionable whether it could have been effective flying at low level in a war against ... the Soviet Union.”

After the British Polaris submarines became operational and Blue Steel was taken out of service in 1970, the Vulcan continued to carry WE.177B in a tactical nuclear strike role as part of the British contribution to Europe's standing NATO forces, although they no longer held aircraft at 15 minutes readiness in peacetime. Two squadrons were also stationed in Cyprus as part of the Near East Air Force and assigned to Central Treaty Organization in a strategic strike role. With the eventual demise of the WE.177B and the Vulcan bombers, the Blackburn Buccaneer, SEPECAT Jaguar, and Panavia Tornado, continued with the WE.177C until its retirement in 1998. While not a like-for-like replacement, the multi-role Tornado interdictor/strike bomber is the successor for the roles previously filled by the Vulcan.

Conventional role

See also: Operation Black Buck

Although the aircraft's armament was primarily a nuclear weapon, in a conventional secondary role it was possible for the Vulcans to carry up to 21 1,000 lb (454 kg) bombs. Since the 1960s, the RAF's Vulcan squadrons had conducted routine training missions in practice for performing conventional bombing missions in addition to nuclear strike missions.

Avro Vulcan
A Vulcan flying over Ascension Island on 18 May 1982

The only combat missions involving the Vulcan took place in 1982 during the Falklands War with Argentina. This was also the only time V-bombers took part in conventional warfare. The missions flown by the Vulcans became known as the Black Buck raids, which flew 3,889 mi (6,259 km) from Ascension Island to Stanley on the Falklands. On 1 May, the first mission was conducted by a single Vulcan that flew over Port Stanley and dropped its bombs on the airfield concentrating on the single runway, with one direct hit, making it unsuitable for fighter aircraft. The Vulcan's mission was quickly followed up by strikes against anti-air installations, flown by British Aerospace Sea Harriers from nearby Royal Navy carriers.

In total, three missions were flown against the airfield, two further missions to launch missiles at radar installations; another two missions were cancelled. Victor tankers conducted the air-to-air refuelling; approximately 1.1 million gal (5 million L) of fuel were used in each mission. At the time, these missions held the record for the world's longest-distance raids. The Vulcan's ECM system was effective at jamming Argentine radars, British aircraft in the vicinity had a greatly reduced chance of coming under effective fire.

Five Vulcans were selected for the operation; their bomb bays were modified, the flight refuelling system that had long been out of use was reinstated, the electronics updated, and new wing pylons fitted to carry an ECM pod and Shrike anti-radar missiles at wing hardpoint locations originally installed for carrying Skybolt missiles. The engineering work began on 9 April.

Avro Vulcan
Avro Vulcan from Operation Black Buck at the National Museum of Flight, showing mission markings and internment in Brazil

Maritime radar reconnaissance

In November 1973, No. 27 Squadron reformed at RAF Scampton in the maritime radar reconnaissance role. Though initially equipped with a number of B.2 aircraft, the Squadron eventually operated nine B.2 (MRR) aircraft. The main external visual difference was the presence of a gloss paint finish, with a light grey undersurface, to protect against sea spray. TFR was not fitted and the aircraft were equipped with LORAN C navigational equipment. Five aircraft were further modified for the Squadron's secondary role of air sampling. These aircraft were distinguishable by the additional hardpoints outside of the underwing Skybolt points upon which could be hung pylons and the air-sampling pods, which had been constructed from de Havilland Sea Vixen drop tanks.

Aerial refuelling role

After the end of the Falklands War in 1982, the Vulcan B.2 was due to be withdrawn from RAF service that year. However, the Falklands campaign had consumed much of the airframe fatigue life of the RAF's Victor tankers. While Vickers VC10 tanker conversions had been ordered in 1979 and Lockheed TriStar tankers would be ordered subsequent to the conflict, as a stopgap measure six Vulcans were converted into single point tankers. The Vulcan tanker conversion was accomplished by removing the jammers from the ECM bay in the tail of the aircraft, and replacing them with a single Hose Drum Unit (HDU). An additional cylindrical bomb-bay tank was fitted, making a total of three, giving a fuel capacity of almost 100,000 lb (45,000 kg).

The go-ahead for converting the six aircraft was given on 4 May 1982. Just 50 days after being ordered, the first Vulcan tanker, XH561, was delivered to RAF Waddington. The Vulcan K.2s were operated by No. 50 Squadron, along with three Vulcan B.2s, in support of UK air defence activities until it was disbanded in March 1984.

Engine test beds

Variants

B.1
The initial production aircraft. First few with straight leading edge, later retrofitted with Phase 2 (kinked) wing. Early examples finished in silver, later changed to "anti-flash" white. Many converted to B.1A standard 1959-1963. Last few unmodified B.1s in RAF service with No. 230 OCU retired by 1966. Last flight by any B.1, an engine testbed XA903, March 1979.
B.1A
The B.1 with an Electronic Countermeasures (ECM) system in a new larger tail cone (as in B.2). Unlike the B.2, the B.1As did not undergo extensive wing strengthening for low-level flying and were withdrawn from service 1966-67.
B.2
Developed version of the B.1. Larger, thinner wing than the B.1 (Phase 2C wing) and fitted with Olympus 201-202 engines of 17,000 lbf (76 kN) each, or Olympus 301 engines of 20,000 lbf (89 kN) each. Uprated electrics with Auxiliary Airborne Power Plant (AAPP) (Auxiliary power unit) and Ram Air Turbine (RAT). ECM similar to B.1A. Terrain-Following Radar (TFR) in nose thimble radome fitted to most aircraft in mid-60s. New Radar warning receiver aerials on tail fin giving it a square top from mid-1970s.
B.2 (MRR)
Nine B.2s converted to Maritime Radar Reconnaissance (MRR). TFR deleted. Five aircraft further modified for Air Sampling Role. Distinctive gloss finish with light grey underside.
K.2
Six B.2s converted for air-to-air refuelling with Mark 17 Hose Drum Unit (HDU) mounted semi-recessed in tail cone. TFR deleted. Fitted with three bomb-bay drum tanks, it was the only mark of Vulcan that could jettison fuel in an emergency.
B.3
Proposed version intended as a long endurance missile carrier capable of carrying up to six Skybolt ALBMs on flights of up to 12 hours duration. Never built.
B.1 B.2 B.3
Length 97 feet 1 inch (29.59 m) 105 feet 11 inches (32.28 m) 110 feet 0 inches (33.53 m)
Height 26 feet 6 inches (8.08 m) 27 feet 2 inches (8.28 m)
Wingspan 99 feet 0 inches (30.18 m) 111 feet 0 inches (33.83 m) 121 feet 0 inches (36.88 m)
Engines 4 x Bristol-Siddeley Olympus 101/102/104 4 x Bristol-Siddeley Olympus 201 or 301 4 x Bristol-Siddeley Olympus 301
Armament 1 x Blue Danube or Yellow Sun;
21 x 1000 lb free-fall bombs
1 x Blue Steel;
21 x 1000 lb free-fall bombs
Up to 6 x Skybolt
Crew 5 5 6

Production

A total of 134 production Vulcans were assembled at Woodford Aerodrome, 45 to the B.1 design and 89 were B.2 models, the last being delivered to the RAF in January 1965.

Contract Date Quantity Variant Notes
6 July 1948 2 Prototypes Two prototypes delivered in August 1952 and September 1953
14 August 1952 25 Vulcan B.1 First flight of production aircraft 4 February 1955, delivered between June 1955 and December 1957.
30 September 1954 20 Vulcan B.1 Delivered between January 1958 and April 1959.
30 September 1954 17 Vulcan B.2 Delivered between September 1959 and December 1960
31 March 1955 8 Vulcan B.2 Delivered between January and May 1961
25 February 1956 24 Vulcan B.2 Delivered between July 1961 and November 1962
22 January 1958 40 Vulcan B.2 Delivered between February 1963 and January 1965, one aircraft not flown and used as a static test airframe
Total 136

Operators

Avro Vulcan
The Vulcan to the Sky Trust's Avro Vulcan XH558
Avro Vulcan United Kingdom

Bases

Avro Vulcan
Avro Vulcans of No 617 Squadron at RAF Cottesmore circa 1975.

V-Bomber dispersal airfields

Further information: List of V Bomber dispersal bases

In the event of transition to war, the V Bomber squadrons were to deploy four aircraft at short notice to each of 26 pre-prepared dispersal airfields around the United Kingdom. In the early 1960s the RAF ordered 20 Beagle Basset communication aircraft to move the crews to dispersal airfields; the importance of these aircraft was only brief, diminishing when the primary nuclear deterrent switched to the Royal Navy's Polaris Missile.

Accidents and incidents

External images
Vulcan B.1 XA897
Avro Vulcan Vulcan B.1 XA897 prior to the accident, stopping over at RAF Khormaksar
Avro Vulcan
The prototype Vulcan VX770 in 1954, retaining the original "pure delta" wing shape

Aircraft on display

Avro Vulcan Media related to Avro Vulcan museum aircraft at Wikimedia Commons

Avro Vulcan
Avro Vulcan XL361 on display at CFB Goose Bay in 1988
Avro Vulcan
Avro Vulcan XL319 on display at North East Aircraft Museum
Avro Vulcan
XH558 performs its first post-restoration public display on 5 July 2008

XH558

Main article: Avro Vulcan XH558

The last airworthy Vulcan (XH558) has been restored to flying condition by the "Vulcan to the Sky Trust" after years of effort and fundraising. The first post-restoration flight, which lasted 34 minutes, took place on 18 October 2007.

The aircraft's airworthiness status was in peril as maintenance funding was in need before the end of February 2010. At the last moment an anonymous benefactor presented £458,000 to the foundation, ensuring its airworthiness for both its 50th birthday and the prospect of a flight performance for the 2012 Summer Olympic Games opening ceremony in London. It is currently based at Doncaster/Sheffield Robin Hood Airport, formerly RAF Finningley.

Specifications

Vulcan B.1

External images
Avro Vulcan B.2 cutaway showing internal compartments and bays
Avro Vulcan Avro Vulcan Cutaway from Flightglobal.com
Avro Vulcan B Mk 2.svg

Data from Polmar, Laming

General characteristics

Performance

Armament

Comparison of variants

Variants compared
B.1 B.1A B.2 B.2 (MRR) K.2
Wingspan 99 ft 5 in (30.30 m) 111 ft 0 in (33.83 m)
Length 97 ft 1 in (29.59 m) 105 ft 6 in (32.16 m) [99 ft 11 in (30.45 m) without probe]
Height 26 ft 6 in (8.08 m) 27 ft 1 in (8.26 m)
Wing area 3,554 sq ft (330.2 m) 3,964 sq ft (368.3 m)
Maximum takeoff weight 167,000 lb (76,000 kg)
185,000 lb (84,000 kg) (operational necessity)
204,000 lb (93,000 kg)
Cruising speed Mach .86 indicated
Maximum speed Mach .95 indicated Mach .93 indicated
(Mach .92 with 301 engines)
Mach .93
indicated
Unknown
Service ceiling 55,000 ft (17,000 m) 45,000 ft (14,000 m) to 56,000 ft (17,000 m)
Electrical system 112V DC 200V AC 3-phase 400 Hz
Emergency electrical
system
Battery Ram air turbine and Airborne Auxiliary Power Plant
Engines 4 × Bristol
Olympus 101, 102 or 104
4 × Bristol
Olympus 104
4 × Bristol Siddeley
Olympus 200-series, 301
4 × Bristol Siddeley
Olympus 200-series
Fuel capacity (main) 9,280 gal (74,240 lb avtur) 9,260 gal (74,080 lb avtur)
Fuel capacity (bomb bay) None 0-1990 gal (15,920 lb avtur) 1990 gal
(15,920 lb avtur)
2985 gal
(23,880 lb avtur)
Powered flying controls 1 x rudder (duplex), 4 x elevators, 4 x ailerons 1 x rudder (duplex), 8 x elevons
Armament 1 × free-fall nuclear bomb or
21 × 1,000 lb (450 kg)
conventional bombs
1 × Blue Steel missile or
1 × free-fall nuclear bomb or
21 × 1,000 lb (450 kg)
conventional bombs
None
Notes
  1. Two extra seats could be fitted for Crew Chiefs if required, for a total of seven crew.
  2. Depended upon oxygen equipment fitted. No airframe limitation on height.
  3. At specific gravity of .8 (8lb/gal).
  4. 2 x 995 gal cylindrical tanks.
  5. 3 x 995 gal cylindrical tanks.

Popular culture

Main article: Avro Vulcan in fiction

See also

Portal icon Royal Air Force portal
Portal icon Aviation portal
Aircraft of comparable role, configuration and era
Related lists

References

Notes

  1. RAF bombers had been traditionally named after inland towns in the British Commonwealth, or towns associated with industry.
  2. A contract for 25 production models had been made in July 1952. The same number of the rival Handley Page design were also ordered.
  3. Writing for the American Institute of Aeronautics and Astronautics, J. Seddon and E. L. Goldsmith noted that "Due to its all-wing shape, small vertical fin, and buried engines, at some angles [The Avro Vulcan] was nearly invisible to radar". While writing about radar systems, authors Simon Kingsley and Shaun Quegan singled out the Vulcan's shape as acting to reduce the RCS. While aviation author Doug Richardson accredits the Vulcan as having been difficult to acquire on radar, he went on to state it was unlikely to have given a great military advantage. In contrast, electronic warfare author and ex-Vulcan AEO Dr Alfred Price maintains "the Vulcan [] possessed a large radar signature."
  4. Some B.2 aircraft armed with Blue Steel had an additional aerial plate fitted between the port tailpipes as the Blue Steel fin, in the lowered position, blanked signals from the starboard side.
  5. Bristol Aero Engines merged with Armstrong Siddeley in 1959 to form Bristol Siddeley which in turn was taken over by Rolls-Royce in 1966.
  6. According to UK parlance of the time, "megaton range" was understood to correspond to 500 kt or greater. The Green Grass warhead had a predicted yield of 500 kt.
  7. Some sources have attested to the existence of a Vulcan B.2A. This designation supposedly referred either to Vulcan B.2s fitted with Olympus Mk 301 engines or those modified to carry the Blue Steel missile. However, irrespective of the role or engine fit, the B.2 was the only official designation except for the MRR and tanker variants.
  8. When flying at a speed of Mach 1.0, the Vulcan suffered a position error of about 0.07.
  9. Avro Chief Test Pilot Tony Blackman notes that when Avro display pilots carried out aerobatics, the displays were followed by a careful but little-known inspection of the inside of the wing's leading edge. Rolls-Royce pilots also carried out aerobatics, but Blackman speculates that Rolls-Royce did not know of the inspections, and VX770 may have already been severely structurally damaged.

Citations

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  5. Wynn 1997, p. 18.
  6. Wynn 1997, pp. 44–46.
  7. Wynn 1997, p. 47.
  8. Gunston, W.T. "The Vulcan Story." Flight, 31 January 1958, p. 143.
  9. Laming 2002, pp. 23, 24.
  10. Laming 2002, p. 26.
  11. Buttler 2003, p. 31.
  12. Wynn 1997, pp. 52–54.
  13. Laming 2002, p. 27.
  14. Laming 2002, p. 29.
  15. Blackman 2007, p. 21.
  16. Laming 2002, p. 32.
  17. Blackman 2007, p. 33.
  18. Laming 2002, p. 43.
  19. Blackman 2007, pp. 38, 40.
  20. Hamilton-Paterson 2010, pp. 18–19.
  21. Wansbrough-White 1995, p. 44.
  22. Brookes and Davey 2009, p. 8.
  23. Blackman 2007, p. 41.
  24. Blackman 2007, pp. 40–48.
  25. Wynn 1997, p. 62.
  26. Blackman 2007, p. 48.
  27. Blackman 2007, pp. 128–129.
  28. Laming 2002, p. 48.
  29. Laming 2002, pp. 217–219.
  30. Wynn 1997, p. 145.
  31. Baxter 1990, p. 46.
  32. 16,000 lb Thrust Flight 15 February 1957 p 200
  33. Laming 2002, p. 62.
  34. Wynn 1997, pp. 315, 316.
  35. Wynn 1997, p. 154.
  36. Wynn 1997, p. 314.
  37. Laming 2002, p. 82.
  38. Wynn 1997, p. 155.
  39. Laming 2002, pp. 218, 219.
  40. Laming 2002, p. 230.
  41. Brookes and Davey, 2009, p. 12.
  42. Pilot's Notes intro. Para. 1.
  43. Pilot's Notes pt. 1, ch. 16, para. 5.
  44. Laming 2002, pp. 63, 64.
  45. Bulman 2001, p. 152.
  46. Wynn 1997, p. 401.
  47. Bulman 2001, pp. 155–161.
  48. Bulman 2001, pp. 149, 150.
  49. Brookes and Davey 2009, pp. 21–23.
  50. Laming 2002, pp. 217–220.
  51. Brookes and Davey 2009, p. 83.
  52. Darling 2007, p. 122.
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  54. Gibson 2011, pp. 117–118.
  55. "Labour research, Volume 51." 1962, p. 20.
  56. Stephens 1992, p. 142.
  57. "Correspondence between the Australian and British Governments concerning the selection of the F-111 over the TSR-2." National Archives of Australia. Retrieved: 11 November 2010.
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  59. Wilson 1989, p. 146.
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  62. Pilot's Notes pt. 1, leading particulars.
  63. Aircrew Manual pt. 1, ch. 2, para. 2.
  64. Wynn 1997, p. 50.
  65. Laming 2002, p. 64.
  66. Pilot's Notes pt. 1, introduction, para 2.
  67. Price, Blackman and Edmonson 2010, p. 102.
  68. Brookes and Davey 2009, p. 65.
  69. Aircrew Manual pt. 1, ch. 8, paras. 1, 2, 48.
  70. Aircrew Manual pt. 1, ch. 8, paras. 3, 12.
  71. Sweetman, Bill. "The Bomber that radar cannot see." New Scientist, 4 March 1982.
  72. Dawson 1957, p. 3.
  73. Seddon and Goldsmith 1999, p. 343.
  74. Kingsley and Quegan 1999, p. 293.
  75. Richardson 2001, p. 56.
  76. Price, Blackman and Edmonson 2010, p. 113.
  77. Wynn 1997, p. 137.
  78. Price, Blackman and Edmonson 2010, p. 112.
  79. Aircrew Manual pt. 1, ch. 14, paras. 1-12.
  80. Pilot's Notes pt. 1, ch. 16, para. 11.
  81. Price, Blackman and Edmonson 2010, pp. 102, 103.
  82. Wynn 1997, p. 321.
  83. Wynn 1997, p. 151.
  84. Bulman 2001, p. 153.
  85. Price, Blackman and Edmonson 2010, p. 106.
  86. Brookes and Davey 2009, p. 57.
  87. Brookes and Davey 2009, pp. 33–35.
  88. Bulman 2001, p. 43.
  89. Brookes and Davey 2009, pp. 36–41.
  90. Bulman 2001, p. 170.
  91. Buttler 2007, p. 72.
  92. Aircrew Manual pt. 1, ch. 7, paras. 1, 7, 10, 24, 48.
  93. Pilot's Notes pt.1, ch. 16, para. 1
  94. Pilot's Notes pt.1, ch. 20, para. 3b
  95. Pilot's Notes pt.1, ch. 16, para. 3b
  96. Pilot's Notes pt. 1, ch. 10.
  97. Aircrew Manual pt.1, ch. 12, para. 1.
  98. "National Archive file AVIA 2347." National Archives. Retrieved: 11 September 2012.
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  100. Pilot's Notes pt. 1, ch. 10, para. 1(a).
  101. Aircrew Manual pt. 1, ch. 7, para. 7.
  102. Aircrew Manual pt. 1, ch. 7, para 70.
  103. Darling 1999, p. 19.
  104. Aircrew Manual pt. 1, ch. 7, para. 77.
  105. Pilot's Notes, ch. 7.
  106. Blackman 2007, pp. 100, 101.
  107. Aircrew Manual, ch. 4.
  108. Aircrew Manual, ch. 7.
  109. Laming 2002, p. 60.
  110. Aircrew Manual pt. 1, ch. 10, paras. 1-3, 48.
  111. Baxter 1990, p. 18.
  112. Baxter 1990, p. 11.
  113. Baxter 1990, p. 13.
  114. "We all love the howl" Vulcan To The Sky Trust, 13 December 2013.
  115. "Will 'howl' of the Vulcan bomber be heard over Bournemouth again?" The Daily Echo, 30 December 2009.
  116. "Vulcan XH558 Awesome Howl Sounds" Youtube, 28 October 2012.
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  118. Laming 2002, p. 108.
  119. Laming 2002, p. 47.
  120. Laming 2002, p. 63.
  121. Baxter 1990, pp. 44–46.
  122. Baxter 1990, p. 50.
  123. "16,000 lb Thrust." Flight, 15 February 1957, p. 200.
  124. Baxter 1990, pp. 50–64.
  125. Lambert, C. M. "Bomex By Vulcan." Flight International, January 1958, p. 66.
  126. Blackman 2007, p. 142.
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  133. Darling 2007, p. 6.
  134. Leitch Air Enthusiast September/October 2003, pp. 55, 58.
  135. Darling 2007, p. 32.
  136. Jackson Wing of Fame 1996, p. 48.
  137. Leitch Air Enthusiast September/October 2003, p. 57.
  138. Darling 2007, p. 19.
  139. Darling 2007, p. 76.
  140. Brookes and Davey 2009, p. 14.
  141. Brookes and Davey 2009, p. 43.
  142. Brookes and Davey 2009, pp. 14–15.
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  144. Darling 2007, p. 116.
  145. Laming 2002, p. 89.
  146. Darling 2007, p. 65.
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Bibliography

Further reading

External links

Source of information: Wikipedia, the free encyclopedia - Disclaimer.

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