Supermarine S.5

The Supermarine S.5 was a 1920s British single-engined single-seat racing seaplane built by Supermarine. Designed specifically for the Schneider Trophy competition, the S.5 was the progenitor of a line of racing aircraft that ultimately led to the iconic Supermarine Spitfire fighter of the Second World War

The S.5 was designed by Reginald Mitchell after the loss of the S.4 before it ever raced. It featured extensive changes from the S.4, possessing numerous unconventional features and making greater use of metal; many of these decisions were made to optimise its racing performance. Due to the short development window, a wooden wing was used rather than an all-metal one. In particular, it possessed a relatively low level of drag for the era.

On 7 June 1927, the first S.5 performed its maiden flight; a total of three aircraft were built. Two S.5s came in 1st and 2nd places at the 1927 Schneider Trophy contest; the type would also participate in the event during subsequent years. On 12 March 1928, one S.5 fatally crashed during an attempt on the world air speed record, killing the pilot Flight Lieutenant Samuel Kinkead. During the 1970s, a full-scale flight-worthy S.5 replica was constructed.

Design and development

The Supermarine S.5 was designed by Reginald Mitchell for the 1927 Schneider Trophy. Following the earlier loss of the S.4 before the 1925 Schneider Trophy was held, Mitchell designed a new monoplane racer. Extensive changes were made between the S.4 and S.5, the principal goal of which was to achieve greater speeds.NACA 1928, p. 1. The design process was heavily influenced by wind tunnel testing, the resulting information from which was kept confidential for some time. The S.5 possessed a particularly low level of drag for a floatplane of the era.NACA 1928, pp. 1-3. Furthermore, the resulting aircraft possessed numerous unorthodox features, some of which were developed to meet specific conditions encountered during high speed air races.NACA 1928, p. 4.

The fuselage of the S.5 was entirely composed of metal, primarily duralumin; the strength of this material enabled the use of semi-monocoque construction, an arrangement that substantially reduced the amount of space taken up by the fuselage. In turn, the cross section of the fuselage could be minimised, to the extent that the pilot was seated on the floor of the fuselage while their shoulders were in contact with the metal skin of the fuselage. Structural elements within the fuselage included loosely-spaced flat U-section formers throughout its length that worked in conjunction with the skin, which functioned as longerons within the stress-resisting structure; in key areas, it was reinforced using fore-and-aft stringers. The forward section of the fuselage had particularly strong frames in order to appropriately support the wing roots, undercarriage struts and function as the attachment point for the anti-lift wire bracing. The latter feature was particularly crucial to the stability of the bracing of both the wings and the sizable floats fitted.NACA 1928, pp. 4-5.

The aircraft was fitted with single-step floats; their structure comprised central longitudinal bulkheads that directly attached to the transverse frames. Several of the longitudinal members were placed between the frames. They were almost entirely composed of duralumin, the centre section of the starboard float was made of steel to permit it to support the primary fuel tank.NACA 1928, p. 5. As there was no room for a fuel tank within the fuselage, all of the aircraft's fuel was carried within the starboard float, which was closer to the aircraft's centreline than the port float; this arrangement gave the aircraft a lower centre of gravity as well as helping to offset engine torque.Lewis 1970, p. 175.NACA 1928, p. 7.

Largely due to a lack of available experimentation time during the aircraft's short development window, the use of an all-metal wing was discounted.NACA 1928, pp. 5-6. Instead, proven wooden construction was used for the wire-braced wings, which possessed spruce spars, spruce-ply ribs and a smooth plywood covering. They were built in two halves along a conventional twin-spar arrangement, albeit with a diagonal member between the wing tips and the fittings for the streamlined bracing wires which stiffened the wing against torsion and reduced the likelihood of encountering aeroelastic flutter.NACA 1928, pp. 6-7. Large radiators were present on the wings; positioned tightly against the wings, they were of a relatively low weight as to avoid incurring excessive wing loading.NACA 1928, p. 6.

The engine was cooled via a somewhat unusual arrangement, using radiators located on the wings in place of the Lamblin type radiators of the S.4; these radiators were made up of corrugated copper sheets and covered a large proportion of the wing surface. Particular attention was paid to the oil system with the aim of minimising fractional losses in the propeller gearing and maximising the aircraft's speed potential.NACA 1928, pp. 7-8. As traditional arrangements were deemed to be insufficient, the oil was cooled via a series of corrugated steel radiators positioned on either side of the fuselage; further cooling of the gears themselves was achieved via several opening in the cowlings of the cylinder block.NACA 1928, p. 8.

The forward bottom portion of the fuselage was reinforced using laminated duralumin to function as the engine bearer, comprising two primary box section bearers that were secured to cradles. One advantage of the scoop-formed engine mounting was a relatively high level of accessibility to the engine. The engine itself was cleanly faired into the fuselage to maximise aerodynamic efficiency.NACA 1928, p. 10.

The flight controls were of a conventional nature, lacking any implementation of variable gearing except for in the actuation of the ailerons. The aircraft was considered to be relatively easy to handle considering its relatively high top speed for the era. The horizontal tail surfaces, which were made of wood, had their control cranks housed within the stern portion of the fuselage; the cranks for the elevator were intentionally offset so they would sufficiently clear the rudder post.NACA 1928, pp. 11-12.

A total of three aircraft were built, one with a direct drive Napier Lion VIIA engine, and the other two with a geared Napier Lion VIIB engine. Lumsden and Heffernan 1989, p. 290.

Operational history

The first aircraft performed its maiden flight on 7 June 1927. The S.5s came 1st and 2nd in the 1927 Schneider Trophy race held at Venice; the winning aircraft (Serial number ''N220'') was flown by Flight Lieutenant Sidney Webster at an average speed of . Andrews and Morgan 1987, p. 186.

One S.5, ''N221'', crashed on 12 March 1928 during an attempt on the world air speed record, killing the pilot Flight Lieutenant Samuel Kinkead, who had flown the Gloster IV in the 1927 Schneider Trophy Race.

Concern over the unreliability of the supercharged Lion powering the Gloster VI led to the High Speed Flight entering one S.5 (''N219'', fitted with a geared Lion engine for the event) along with the two S.6s for the 1929 Schneider contest. The S.5, flown by Flight Lieutenant D'Arcy Greig, finished third in 46 minutes and 15 seconds at a speed of , behind the winning S.6 flown by Flying Officer H. Richard Waghorn and a Macchi M.52. Andrews and Morgan 1987, pp. 192–193.

Replica

Ray Hilborne of Leisure Sports designed and built a full-scale S.5 replica which flew for the first time on 28 August 1975. The replica, powered by a Continental IO-360, used an all-wood construction and incorporated modifications to the wing to lower the stalling speed, water rudders, a slightly wider cockpit and overall weight reduction to an all-up weight of just , less than half that of the S.5. Hall 1976, p. 576.

Popular culture

In the song "Bill Hosie" by Archie Fisher, the protagonist rebuilds a Supermarine S.5 that survived the 1927 Schneider Trophy contest. The aircraft, race, and trophy are referred to throughout the song.

Operators

;
* Royal Air Force
** High Speed Flight

Specifications (N220)

See also

References

Citations

Bibliography

* Andrews, C.F. and E.B. Morgan. ''Supermarine Aircraft since 1914, 2nd edition''. London: Putnam, 1987. .
* Green, William, ed. "Supermarine's Schneider Seaplanes." ''Flying Review International'', Volume 10, No. 11, July 1967.
* Hall, John. "Supreme Supermarine." ''Aeroplane Monthly'', Volume 4, No. 11, November 1976.
* ''The Illustrated Encyclopedia of Aircraft (Part Work 1982–1985)''. London: Orbis Publishing, 1985.
* Jackson, A.J. ''British Civil Aircraft since 1919''. London: Putnam, 1988. .
* Lewis, Julian
''Racing Ace - The Fights and Flights of 'Kink' Kinkead DSO DSC* DFC*.''
Barnsley, UK: Pen & Sword, 2011. .
*
* Lumsden, Alec and Terry Heffernan. "Per Mare Probare, Part 15," ''Aeroplane Monthly'', Volume 17, No. 5, May 1989.
* Shelton, John
''Schneider Trophy to Spitfire - The Design Career of R.J. Mitchell''.
Yeovil, UK: Haynes Publishing, 2008. .

"Supermarine S.5 Seaplane (British) : Winner of the 1927 Schneider Cup Race"
''National Advisory Committee for Aeronautics'', 1 March 1928. NACA-AC-67, 93R19940.

External links

Profile - The Schneider Trophy winning Supermarine S.5 - Aeroplane Monthly

1927 Schneider Trophy

Supermarine S.5—A British Legend Reborn
the project to build a replica S.5 for the centenary of the 1927 contest

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Schneider Trophy
1920s British sport aircraft
Floatplanes
S.5
Low-wing aircraft
Single-engined tractor aircraft
Aircraft first flown in 1927