Supermarine Walrus
| Walrus | |
|---|---|
 |
|
| Supermarine Walrus, 1935 | |
| Role | Amphibious reconnaissance aircraft |
| National origin | United Kingdom |
| Manufacturer | Supermarine |
| Designer | R. J. Mitchell |
| First flight | 21 June 1933 |
| Introduction | 1935 |
| Primary users |
Royal Navy Irish Air Corps Royal Air Force Royal Australian Air Force |
| Produced | 1936–1944 |
| Number built | 740 |
| Developed from | Supermarine Seagull |
The Supermarine Walrus (originally known as the Supermarine Seagull V) was a British single-engine amphibious biplane reconnaissance aircraft designed by R. J. Mitchell and first flown in 1933. It was operated by the Fleet Air Arm (FAA) and also served with the Royal Air Force (RAF), Royal Australian Air Force (RAAF), Royal New Zealand Navy (RNZN) and Royal New Zealand Air Force (RNZAF). It was the first British squadron-service aircraft to incorporate in one airframe a fully retractable main undercarriage, completely enclosed crew accommodation and all-metal fuselage.
Designed for use as a fleet spotter to be catapult launched from cruisers or battleships, the Walrus was later employed in a variety of other roles, most notably as a rescue aircraft for downed aircrew. It continued in service throughout the Second World War.
The Walrus was initially developed as a private venture in response to a 1929 Royal Australian Air Force (RAAF) requirement for an aircraft to be catapult-launched from cruisers, and was originally called the Seagull V, although it only resembled the earlier Supermarine Seagull III in general layout. Construction was started in 1930 but owing to Supermarine's other commitments it was not completed until 1933.
The single-step hull was constructed from aluminium alloy, with stainless-steel forgings for the catapult spools and mountings. Metal construction was used because experience had shown that wooden structures deteriorated rapidly under tropical conditions. The wings, which were slightly swept back, had stainless–steel spars and wooden ribs and were covered in fabric. The lower wings were set in the shoulder position with a stabilising float mounted under each one. The horizontal tail-surfaces were positioned high on the tail-fin and braced on either side by N struts. The wings could be folded on ship, giving a stowage width of 17 feet 6 inches (5.33 m). The single 620 hp (460 kW) Pegasus II M2 radial engine was housed at the rear of a nacelle mounted on four struts above the lower wing and braced by four shorter struts to the centre-section of the upper wing. This powered a four-bladed wooden propeller in pusher configuration. The engine nacelle contained the oil tank, arranged around the air intake at the front of the nacelle to act as an oil cooler, and electrical equipment and had a number of access panels for maintenance. A supplementary oil cooler was mounted on the starboard side. Fuel was carried in two tanks in the upper wings. The pusher configuration had the advantages of keeping the engine and propeller further out of the way of spray when operating on water and reducing the noise level inside the aircraft. Also, the moving propeller was safely away from any crew standing on the front deck, which would be done when picking up a mooring line. The engine was offset by three degrees to starboard, to counter any tendency of the aircraft to yaw due to unequal forces on the rudder caused by the vortex from the propeller.
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