|Artist's impression of the Miles M.52|
|Role||Experimental supersonic aircraft|
|National origin||United Kingdom|
|Designer||Don L. Brown|
The Miles M.52 was a turbojet-powered supersonic research aircraft project designed in the United Kingdom in the mid-1940s. In October 1943, Miles Aircraft was issued with a contract to produce the aircraft in accordance with Air Ministry Specification E.24/43. The programme was highly ambitious for its time, aiming to produce an aircraft and engine capable of unheard-of speeds of at least 1,000 miles per hour (1,600 km/h) during level flight, and involved a very high proportion of cutting-edge aerodynamic research and innovative design work.
Between 1942 and 1945, all work on the project was undertaken with a high level of secrecy. In February 1946, the programme was terminated by the new Labour government of Clement Attlee, seemingly due to budgetary reasons, as well as a disbelief held by some ministry officials on the viability of supersonic aircraft in general. In September 1946, the existence of the M.52 was revealed to the general public, leading to calls for official explanation as to why the project had been terminated and derision of the decision. The Air Ministry controversially decided to revive the design, but as a series of unmanned rocket-powered 30 per cent scale models instead of the original manned full-scale aircraft that had been previously under development. These unmanned scale models were air-launched from a modified de Havilland Mosquito mother ship.
During one successful test flight, Mach 1.38 was achieved by a scale model in normally controllable transonic and supersonic level flight, a unique achievement at that time which validated the aerodynamics of the M.52. At that point, the ministry had cancelled that project and issued a new requirement, which would ultimately result in the English Electric Lightning interceptor aircraft. Work on the afterburning version of the Power Jets W.B.2/700 turbojet was also cancelled and the Power Jets company was incorporated into the National Gas Turbine Establishment. Many believe the design and the research gained from the M.52 was shared with the American company Bell Aircraft.
Prior to the Second World War, conventional wisdom throughout the majority of the aviation industry was that manned flight at supersonic speeds, those in excess of the sound barrier, was next to impossible, mainly due to the apparently insurmountable issue of compressibility. During the 1930s, few researchers and aerospace engineers chose to explore the field of high speed fluid dynamics; notable pioneers in this area were the German aerospace engineer Adolf Busemann, British physicist Sir Geoffrey Taylor, and British engine designer Sir Stanley Hooker. While Germany gave considerable attention to exploring and implementing Busemann's theories on the swept wing and its role in drag-reduction during high speed flight, both Britain and the United States overlooked this research on the whole. It was only by 1944 that information regarding the rocket-propelled Messerschmitt Me 163 or the jet-propelled Me 262, both having been equipped with swept wings, did wider attitudes on its merits begin to change. Prior to this point, the British Air Ministry had already launched a research programme of its own.
In Autumn 1943, the Air Ministry issued a call for nothing less than a revolutionary aircraft in the form of Air Ministry Specification E.24/43. The Specification sought to produce a jet-powered research aircraft for the ambitious purpose of being able to reach supersonic speeds, which was faster than any aircraft had ever flown at that point. It called for an "aeroplane capable of flying over 1,000 miles per hour (1,600 km/h) in level flight, over twice the existing speed record at that time, along with the ability to climb to 36,000 feet (11,000 m) in 1.5 minutes." Aviation author Derek Wood described E.24/43 as being "the most far-sighted official requirement ever to be issued by a Government department...a complete venture into the unknown with engine, airframe, and control techniques beyond anything remotely considered before". In fact, the specification had only been intended to produce a British aircraft that could match the supposed performance of an apparently existing German aircraft: the 1,000 mph (supersonic) requirement had resulted from the mistranslation of an intercepted communication which had reported that the maximum speed to have been 1,000 km/h (subsonic). This report is believed to have been referring to either the Messerschmitt Me 163A or the Me 262.
The Miles Aircraft company had its beginnings in the 1920s and made a name for itself during the 1930s by producing affordable ranges of innovative light aircraft, perhaps the best known amongst these being the Miles Magister and Miles Master trainers, large numbers of both types seeing heavy use by the RAF for fighter pilot training. Although the company's products were relatively low-technology trainers and light aircraft, and did not include any jet-propelled aircraft, Miles had a good relationship with the Air Ministry and the Royal Aircraft Establishment (RAE), and had submitted several proposals for advanced aircraft in response to ministry specifications. Miles was invited to undertake a top-secret project to meet with the requirements of Specification E.24/43; thus begin Miles' involvement in high speed aviation. The decision to involve the company has been alleged to have been partially in order to resolve a dispute about a separated contract that had been allegedly mishandled by the Ministry of Aircraft Production; Woods states that the Minister of Aircraft Production Sir Stafford Cripps had been impressed by Miles' designs and development team and thus favoured it to meet the specification.
Fred Miles of Miles Aircraft was summoned to the Ministry of Aircraft to meet with researcher Ben Lockspeiser for the latter to outline the difficulties and challenges involved in developing such an aircraft. The project required the highest level of secrecy throughout, Miles being responsible for the development and manufacturing of the airframe while Frank Whittle's Power Jets company developed and produced a suitable engine to equip the aircraft. For this project, Miles would cooperate with and receive assistance from the Royal Aircraft Establishment (RAE) in Farnborough and the National Physical Laboratory. On 8 October 1943, Miles received the formal go-ahead to proceed from Air Marshal Ralph Sorley, and immediately set about establishing appropriate secure facilities for the project.
Faced with limited amounts of existing relevant information from available sources upon which to base the aircraft's design, Miles turned to the field of ballistics instead. He had reasoned that, as it was widely known that bullets could attain supersonic speeds, aerodynamic properties that would enable an aircraft to be capable of becoming supersonic would likely to be present amongst such shapes. In particular, as a result of studying this design data, the emerging aircraft would feature both a conical nose and very thin elliptical wings complete with sharp leading edges. This contrasted against many early jet aircraft, which were furnished with round noses, thick wings and hinged elevators, resulting in these aircraft possessing critical Mach numbers that were below the speed of sound and thus were less suitable for research into high subsonic speeds (in dives) than the earlier Supermarine Spitfire with its thinner wings. In 1943, RAE tests conducted using Spitfires had proved that drag was the main factor that would need to be addressed by high-speed aircraft.
Another critical addition was the use of a power-operated stabilator, also known as the all-moving tail or flying tail, a key to supersonic flight control which contrasted with traditional hinged tailplanes (horizontal stabilizers) connected mechanically to the pilot's control column. Conventional control surfaces became ineffective at the high subsonic speeds then being achieved by fighters in dives, due to the aerodynamic forces caused by the formation of shockwaves at the hinge and the rearward movement of the centre of pressure, which together could override the control forces that could be applied mechanically by the pilot, hindering recovery from the dive. A major impediment to early transonic flight was control reversal, the phenomenon which caused flight inputs (stick, rudder) to switch direction at high speed; it was the cause of many accidents and near-accidents. An all-flying tail is considered to be a minimum condition of enabling aircraft to break the transonic barrier safely without a loss of pilot control. The M.52 was the first instance of this solution, which has since gone on to be universally applied upon high-speed aircraft.
An initial version of the aircraft was to be test-flown using Frank Whittle's latest engine, the Power Jets W.2/700. This engine, which was envisaged to be capable of providing 2,000 lb of thrust, calculated to be capable of providing subsonic performance; when flown in a shallow dive, it would also be capable of transonic flight. Wood described the engine as being "remarkable as it incorporated ideas far ahead of its time". In order to get the M.52 to achieve supersonic speeds, the installation of projected further development of the W.2/700 engine would be necessary.
This further advanced model of the engine, intended to be a fully supersonic version of the aircraft, was partially achieved by the incorporation of a reheat jetpipe - also known as an afterburner. Extra fuel was to be burned in the tailpipe to avoid overheating the turbine blades, making use of unused oxygen present in the exhaust. To supply more air to the afterburner than could move through the fairly small engine, an augmentor fan powered by the engine was to be fitted behind the engine to draw air around the engine via ducts. These changes were estimated to provide for an addition 1,620 lb of thrust when at 36,000 ft and 500 mph; much greater thrust gains were believed to have resulted from travelling at speeds in excess of 500 mph.
The M.52's design underwent many changes during development due to the uncertain nature of the task. The overseeing committee was concerned that the biconvex wing would not give sufficient altitude for testing the aircraft in a dive. The thin wing could have been made thicker if required, or a section added to increase the wing span. As the project progressed, an increase in total weight led to concerns that power would be insufficient; thus, the adoption of rocket assistance or extra fuel tanks were considered. Another proposed measure was that the M.52 be adapted to become a parasite aircraft, launching at high altitude from beneath a large bomber serving as a mother ship. The calculated landing speed of 160 to 170 miles per hour (260 to 270 km/h) (comparable with modern fighters but high for that time) combined with its relatively small undercarriage track was another concern; however, this arrangement was accepted.
During 1943, a single Miles M.3B Falcon Six light aircraft, which had been previously used for wing tests by the RAE, was provided to Miles for purpose of performing low-speed flight testing work on the project. A full size wooden model of the M.52 wing, test instrumentation, and a different undercarriage were fitted to this aircraft. Owing to the wing's thinness and sharp leading and trailing edges somewhat resembling a razor blade, the aircraft was nicknamed the "Gillette Falcon". On 11 August 1944, this low-speed demonstrator performed its maiden flight. These tests found the wing to present favourable aileron function, but also indicated that landing without flaps to be more difficult than its contemporaries. Compared with a standard Falcon Six, wing area was reduced by about 12 per cent; it had the effect of increasing the landing speed by over 50 per cent from 40 to 61 mph (64 to 98 km/h), higher than any prior aircraft.
For high speed testing, the flying tail of the M.52 was fitted to the fastest aircraft then available, a Supermarine Spitfire. RAE test pilot Eric Brown stated that he tested this aircraft successfully during October and November 1944; on one such flight, he managed to attain a recorded speed of Mach 0.86 during a dive from high altitude. The flying tail was also fitted to the "Gillette Falcon", which proceeded to conduct a series of low speed flight tests at the RAE in April 1945. (Personal letter from Eric Brown to me in 2003 confirmed that the all moving stabilizer was never fitted to the Spitfire)
Due to the limited capability of existing wind tunnel facilities in Britain, Miles elected to manufacture their own wind tunnel, which was used to conduct the first M.52 aerodynamic tests. This undertaking necessitated Miles to construct their own on-site small-scale foundry, both due to secrecy requirements and to produce components of sufficient tolerance. By August 1945, the design of the M.52 had been firmly established and development had proceeded to an advanced stage. By early 1946, 90 per cent of the detailed design work had been finished, the component assembly programme was well underway, while the jigs and innovative augmentor fan had been manufactured; a maiden flight of the first M-52 prototype had been anticipated to occur that summer.
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The Miles M.52 was to have been supersonic research aircraft, envisioned to be capable of achieving 1,000 miles per hour (1,600 km/h) in level flight. In order to achieve what was at the time previously unachievable speeds, a very high number of advanced features were incorporated into the design of the M.52; many of which had been the product of detailed study and acquired knowledge of supersonic aerodynamics. Wood summarises the qualities of the M.52's design as possessing "all the ingredients of a high-performance aircraft of the late fifties and even some of the early sixties".
The fuselage of the M.52 was cylindrical and, like the rest of the aircraft, was constructed of high tensile steel with light-alloy covering. The fuselage had the minimum cross-section allowable around the centrifugal engine with fuel tanks in a saddle-like arrangement placed over the upper area around it. The engine was positioned with its center of gravity coincident with that of the aircraft and the wings were attached to the main structure just aft of the engine. The use of a shock cone in the nose was another key design choice; the inlet cone slowed incoming air to the subsonic speeds determined by the engine, but with lower losses than a subsonic aircraft pitot intake. A retractable tricycle undercarriage was used. The nose wheel was positioned close to the pilot's feet and the main wheels were fitted onto the main fuselage, folding out under the wings when deployed.
The M.52 had very thin wings of biconvex section, which had been first proposed by Jakob Ackeret, as they gave a low level of drag. These wings were so thin that they were known to test pilots as 'Gillette' wings, named after the brand of razor. The wing tips were "clipped" to keep them clear of the conical shock wave that was generated by the nose of the aircraft. Both wide-chord ailerons and split-flaps were fitted to the wings. As a high speed wing of this shape and size had not been tested before, Miles produced a full-scale wooden model of the wing for aerodynamic testing purposes; other representative portions of the aircraft, such as the tailplane, would be similarly produced and underwent low-speed flight testing.
The Power Jets W.2/700 turbojet engine was intended to be the first powerplant for the M.52. Initial aircraft would have been powered by a less-capable 'interim' model of the W.2/700 and thus be limited to subsonic speeds only; it did not feature either the afterburner or the additional aft fan that were to be present on the projected more advanced version with which later-built M.52s would have been equipped. In addition to the W.2/700 engine, a centrifugal-flow jet engine, designs were prepared for the M.52 to be fitted with a variety of different engines and types of propulsion, including what would become the newer Rolls-Royce Avon axial-flow jet engine, and a liquid-fuel rocket motors.
The M.52's single pilot, who, for the intended first flight, would have been test pilot Eric Brown, would have flown the aircraft from a small cockpit which was set inside the shock cone at the nose of the aircraft. The pressurised cockpit, in which the pilot would have had to fly the aircraft in a semi-prone position, was complete with a curved windscreen that was aligned with the contours of the bullet-shaped nose. In the event of an emergency, the entire section could be jettisoned, the separation from the rest of aircraft being initiated via multiple cordite-based explosive bolts. Air pressure would force the detached capsule off the fuselage while a parachute would slow its descent; during the capsule's descent, the pilot would bail out at a lower altitude and then parachute to safety. In order to serve its role as a research aircraft, the M.52 was to be equipped with comprehensive flight instrumentation, including automated instrument recorders and strain gauging throughout the structure connected to an oscilloscope.
In 1944, design work was considered 90 per cent complete and Miles was told to proceed with the construction of a total of three prototype M.52s. Later that year, the Air Ministry signed an agreement with the United States to exchange high-speed research and data. Miles Chief Aerodynamicist Dennis Bancroft stated that the Bell Aircraft company was given access to the drawings and research on the M.52; however, the U.S. reneged on the agreement and no data was forthcoming in return. Unknown to Miles, Bell had already started construction of a rocket-powered supersonic design of their own but, having adopted a conventional tail for their aircraft, were battling the problem of control. A variable-incidence tail appeared to be the most promising solution; the Miles and RAE tests supported this conclusion. Later, following the conversion of the aircraft's tail, pilot Chuck Yeager practically verified these results during his test flights, and all subsequent supersonic aircraft would either have an all-moving tailplane or a delta wing.
In February 1946, Miles was informed that by Lockspeiser of the immediate discontinuation of the project and to cease work on the M.52. Frank Miles later stated of this decision: "I did not know what to say or think when this extraordinary decision was sprung upon me, without warning of any kind. At our last official design meeting all members, including the Ministry and Power Jets' representatives, had been cheerful and optimistic". According to Frank Miles, when he approached Lockspeiser for reasons behind the cancellation, he was informed that it was due to economic reasons; Lockspeiser also stated his belief that aeroplanes would not fly supersonically for many years and may not ever do so. By this point, the postwar Labour government, headed by Clement Attlee, had implemented dramatic budget cuts in various areas, which may have provided an inducement for the cancellation of the M.52, which was projected to involve considerable cost. According to Wood, "the decision not to go ahead was purely a political one made by the Attlee Government".
In February 1946, around the same time as the termination of the M.52's development, Frank Whittle resigned from Power Jets, stating that this was due to his disagreement with official policy. At the point of cancellation, the first of the three M.52s had been 82 per cent completed and it had been scheduled to commence the first test flights within only a few months. The test programme would have involved the progressive testing and development of the M.52 by the RAE, initially without reheat installed. The ultimate aim of the tests would have been to have achieved Mach 1.07 by the end of 1946.
Miles made a last ditch attempt to revive the project, submitting a proposal for a single near-complete M.52 prototype to be outfitted with a captured German rocket engine and automated controls, eliminating the requirement for a pilot to be on board. However, this proposal was rejected. Due to the project falling under the Official Secrets Act, the existence of the M.52 was unknown to the wider British public; thus, neither the nation nor the world knew that a supersonic aircraft had nearly been built, nor of its unceremonious termination. The Ministry repeatedly refused to allow Miles to hold press conferences on the M.52 and, while conducting its own press conference on the topic of high-speed flight on 18 July 1946, the Ministry made no mention of the project at all. It wasn't until September 1946 that the Ministry allowed Miles to announce that the existence of the M.52 and of its cancellation.
Upon the announcement of the M.52's existence, there was a huge amount of press interest in the story, who pressured the government to provide more detail on the cancellation. A spokesman for the Ministry of Supply eventually commented on the topic, suggesting that other approaches had been suggested by later research that were being pursued in place of the M.52. According to Wood, the response from the Ministry was "a complete smokescreen...it was unthinkable to admit that supersonic expertise was non-existent. Lockspeiser's role in cancelling the M.52 became public knowledge, leading to his decision being derided in by the press as "Ben's blunder".
It was not until February 1955 did another official reason for the M.52's cancellation emerge; a white paper issued that month stated that "the decision was also taken in 1946 that, in light of the limited knowledge then available, the risk of attempting supersonic flight in manned aircraft was unacceptable high and that our research into the problems involved should be conducted in the first place by means of air launched models". This same paper acknowledged that the termination decision had seriously delayed the advancement of aeronautical progress by Britain. 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.
In 1947, Miles Aircraft Ltd entered receivership and the company was subsequently re-structured; its aircraft assets including the design data for the M.52 were acquired by Handley Page.
Instead of a revival of the full-scale M.52, the government decided to institute a new programme involving expendable, pilotless, rocket-propelled missiles; it was envisioned that a total of 24 flights would be performed by these models, which would explore six different wing and control surface configurations, including alternative straight wing and swept wing arrangements. Wood referred to the failure to revive the full-scale aircraft as "at one stroke Britain had opted out of the supersonic manned aircraft race". The contract for the expendable missiles was not issued to Miles but to Vickers-Armstrongs, whose design team was led by noted British engineer and inventor Barnes Wallis. While the base design work was conducted by Wallis' team, engine development was performed by the RAE itself. The product of these efforts was a 30 per cent scale radio-controlled model of the original M.52 design, powered by a single Armstrong Siddeley Beta rocket engine, fuelled by a mix of high-test peroxide.
In total, there had been an overall interval of 15 months between the termination of the manned M.52 and the emergence of the first flight-ready rocket-powered test model. As envisioned, the test model would be launched from altitude via a flying mother ship in the form of a modified de Havilland Mosquito; it was installed upon a purpose-built rack installed in between the aircraft's bomb bay doors. Shortly after launch, its onboard autopilot was to level the model out prior to the rocket motor being started. Within 70 seconds of being released, the model was envisioned to be capable of achieving a speed of Mach 1.3 (880mph); it was then to descend into the ocean below without any chance of recovery. The acquired data on each flight was to be provided via transmitted radio telemetry, which was received by a ground station based on the Scilly Isles.
On 8 October 1947, the first launch of a test model occurred from high altitude; however, the rocket unintentionally exploded shortly following it release. Only days later, on 14 October, the Bell X-1 broke the sound barrier. There was a flurry of denunciation of the government's decision to cancel the project, with the Daily Express taking up the cause for the restoration of the M.52 programme, to no effect. On 10 October 1948, a second rocket was launched, and the speed of Mach 1.38 was obtained in stable level flight, a unique achievement at that time. By this point, the X-1 and Yeager had already reached M1.45 on 25 March of that year. Instead of diving into the sea as planned, the model failed to respond to radio commands and was last observed (on radar) heading out into the Atlantic. Following that successful supersonic test flight, further work on this project was cancelled, being followed up immediately by the issue of Ministry of Supply Experimental Requirement ER.103.
One of the official reasons given for the cancellation was "the high cost for little return". Wood commented of the model programme: "with the money thus wasted the piloted M.52 could have been completed and flown and a great store of invaluable information obtained...the pilot was shown to be essential for any worthwhile development process and a well designed test-bed aircraft to be a sine qua non for full-scale knowledge".
Many important design principles that were incorporated in the M.52 did not reappear until the mid- to late 1950s, with the development of truly supersonic aircraft such as the Fairey Delta 2, and the English Electric P.1 which became the highly regarded English Electric Lightning. And the X-1, D-558-2, F-100, F-101, F-102, F-104, Mig-19 etc. in the 40s and early 50s. Note also that the wing design of the M.52 was similar to the supersonic Wasserfall German rocket. Both of those aircraft were developed in response (initially) to requirement ER.103 of 1947, informed by the knowledge gained from the M.52 aircraft and missile research projects together with German experimental data.
Data from Brown
- Crew: 1
- Length: 28 ft (8.5 m)
- Wingspan: 27 ft (8.2 m)
- Height: ()
- Wing area: 108.1 ft² (10.04 m²)
- Loaded weight: 7,710 lb (3,500 kg)
- Max. takeoff weight: 8,200 lb (3,720 kg)
- Powerplant: 1 × Power Jets W.2/700 turbojet (fitted with augmentor and afterburner), 4,000 lbf (17.8 kN)
- Maximum speed: 1,000 mph (1,600 km/h) at 36,000 ft (11,000 m)
- Stall speed: 170 mph (274 km/h)
- Service ceiling: 50,000 ft (15,240 m)
- Rate of climb: to 36,000 ft (11,000 m) in 1.5 minutes
- Wing loading: 55.4 lb/sq ft ()
- Aircraft of comparable role, configuration and era
- Wood 1975, p. 27.
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- "High Speed Research." The Aeroplane Spotter, 19 October 1946. Retrieved: 12 October 2009.
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- Brown, Eric. The Miles M.52: Gateway to Supersonic Flight. Stroud, Gloucestershire, UK: The History Press, 2012. ISBN 978-0-7524-7014-6.
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- Temple, Julian C. Wings Over Woodley - The Story of Miles Aircraft and the Adwest Group. Bourne End, Bucks, UK: Aston Publications, 1987. ISBN 0-946627-12-6.
- Wood, Derek. Project Cancelled. Indianapolis: The Bobbs-Merrill Company Inc., 1975. ISBN 0-672-52166-0.
- Yeager, Chuck et al. The Quest for Mach One: A First-Person Account of Breaking the Sound Barrier. New York: Penguin Studio, 1997. ISBN 0-670-87460-4.
|Wikimedia Commons has media related to Miles M.52.|
- Faster than Sound - Nova documentary
- transcript of the Nova programme
- Jets45 Histories
- A video of a modern radio controlled model replica of the M.52 flying
- Eric "Winkle" Brown talks about the M.52 in 2008
- Museum of Berkshire Aviation: "The M.52 Story"
- "High Speed Research" (pdf download). The Aeroplane Spotter, 19 October 1946.
- "The 1,000-m.p.h. M.52." Flight, 12 September 1946.
- "Miles on supersonic flight." Flight, October 1946, p. 355.
- Supersonic Approach by H. F. King, M.B.E.Flight 3 April 1947
- "Britain Goes Supersonic", January 1946, Popular Science
- Ministry of Supply report "Flight Trials of a Rocket-propelled Transonic Research Model : The R.A.E.-Vickers Rocket Model"
- "Transonic Research" a 1946 Flight article on the M.52-based Vickers test rocket.