Percival P.74

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P.74

Hunting Percival P.74 being readied for flight testing c. 1956
Type Helicopter
Manufacturer Percival Aircraft Company
Status Cancelled 1956
Number built 1

The Percival P.74 (later Hunting Percival P.74) was a British experimental helicopter design in the 1950s that was based on the use of tip-jet powered rotors. Although innovative, the tip-rotor concept literally failed to get off the ground in the P.74, doomed by its inadequate power source. Rather than being modified, the P.74 was ignominiously towed off the airfield and scrapped.[1]

Contents

[edit] Design and development

In 1951, a Helicopter Division was formed by Percival Aircraft Company and design work commenced on a medium-sized helicopter designated P.74. This experimental helicopter had a teardrop-shaped fuselage with a two-seat cockpit in the nose and a large cabin running the full length of the fuselage. Beneath the cabin floor were two Napier Oryx gas generators which fed compressed air to the tips of the three rotor blades through triple ejector ducts. The rotor blades used ailerons on the trailing edges with pitch control achieved by a screw jack. The unusual engine location necessitated exhaust pipes coming through the cabin wall between the rows of seats, creating an unenviable amount of din and heat for the intended passengers.

The P.74 prototype (designated the Hunting Percival P.74 after the company name change was instituted in 1954) was completed in the spring of 1956, and given the military serial number XK889. The final product looked decidedly ungainly with the large bulbous fuselage tapering to a tiny "tailcone" that featured an equally tiny tail rotor (deemed sufficient for control since there was no torque from the tip-rotors). The undercarriage consisted of four wheels on splayed-out stubs with the front two wheels being castering.

[edit] Testing and evaluation

Hunting Percival P.74 c. 1956
Hunting Percival P.74 c. 1956

Ground testing in a static rig commenced in 1956 but the Oryx engines failed to develop full power and maximum gas flow. Even with modifications to the power units, the first flight was aborted when the P.74 failed to fly. This may have been providential as there were no escape provisions for the two pilots.[2] The only entrance door was located at the rear on the port side. The primary test pilot was famously quoted as saying the hapless P.74 had "the cockpit, flying controls and engine controls... designed without any input from a pilot."[2]

It was planned to fit a more powerful Rolls-Royce RB.108 turbine and a further development of a ten-passenger (P.105)[2] variant was on the "drawing boards" when the rationalisation of the helicopter industry later that year resulted in the P.74 project being cancelled and the prototype scrapped.

[edit] Specifications (P.74)

General characteristics

  • Crew: 2
  • Capacity: 8 passengers in two rows
  • Length: ()
  • Rotor diameter: 53 ft (15.76 m)
  • Height: ()
  • Loaded weight: 7,750 lb (3,515 kg)
  • Max takeoff weight: lb (kg)
  • Powerplant: 2× Napier Oryx No. 1 gas generator, 754 shp (563 kW) each

Performance

[edit] See also

Comparable aircraft

[edit] References

[edit] Notes

  1. ^ Winchester 2005, p. 230.
  2. ^ a b c Winchester 2005, p. 231.

[edit] Bibliography

  • Winchester, Jim. The World's Worst Aircraft: From Pioneering Failures to Multimillion Dollar Disasters. London: Amber Books Ltd., 2005. ISBN 1-904687-34-2.

[edit] External links

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