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For the 1924 aeroplane, see Westland Widgeon (fixed wing){|class="infobox " style="float: right; clear: right; width: 315px; border-spacing: 2px; text-align: left; font-size: 90%;"

! colspan="2" style="text-align: center; font-size: large; padding-bottom: 0.3em;" | Widgeon |-

| colspan="2" style="text-align: center; font-size: 90%; line-height: 1.5em;" |

|- |colspan="2" style="border-bottom: 1px solid #aaa;text-align:center;" |Westland WS-51A Widgeon on display at the Helicopter Museum (Weston) |-


! Role | Helicopter |-

! Manufacturer | Westland Aircraft |-


! First flight | 23 August 1955 |-




! Number built | 12 new built plus 3 conversions[1] |-


! Developed from | Westland WS-51 Dragonfly |-


|}

The Westland Widgeon helicopter was a private venture by Westland Aircraft as an improvement on the Westland WS-51 Dragonfly.

Design and development[edit | edit source]

Westland Aircraft decided to make a private venture improvement on the Westland WS-51 Dragonfly, which was a licensed Sikorsky design, helicopter by increasing the cabin capacity and replacing the Dragonfly's rotor head, blades and gearbox with the units used in the Westland Whirlwind. Three Dragonfly Series 1As were converted to WS-51 Series 2 Widgeons, and the first one flew on 23 August 1955.

There was a plan to take up to 24 existing Fleet Air Arm Dragonflies to Dragonfly HC.7 standard (as the Naval Widgeon was to become) but this was abandoned and it contributed to the decision to stop progress.[Clarification needed]


Operators[edit | edit source]

 Brazil
Sri Lanka Ceylon
 Hong Kong
 Jordan
 United Kingdom

Specifications (Widgeon)[edit | edit source]

Data from Westland Aircraft since 1915[1]

General characteristics

  • Crew: 1
  • Capacity: 4 passengers
  • Length: 41 ft 10 in (12.75 m)
  • Rotor diameter: 49 ft 2 in (14.99 m)
  • Height: 13 ft 4 in (4.07 m)
  • Disc area: 1,898 ft² (176.4 m²)
  • Empty weight: 4,322 lb (1,969 kg)
  • Loaded weight: 5,900 lb (2,682 kg)
  • Powerplant: 1 × Alvis Leonides 521/2 nine-cylinder air-cooled radial engine, 520 hp (388 kW)

Performance

  • Maximum speed: 109 mph (95 knots, 175 km/h) at sea level
  • Range: 310 mi[7] (270 nmi, 500 km)
  • Service ceiling: 11,800 ft (3,600 m)
  • Rate of climb: 700 ft/min (3.6 m/s) at sea level

See also[edit | edit source]

References[edit | edit source]

Notes[edit | edit source]

  1. 1.0 1.1 James 1991, p. 320.
  2. Flight International 13 July 1967, p. 58.
  3. Flight International 13 July 1967, p. 60.
  4. Iliffe-Moon, Peter (17 May 1973). "The unarmed air force". p. 759. http://www.flightglobal.com/pdfarchive/view/1973/1973%20-%201297.html. 
  5. Flight International 13 July 1967, p. 62.
  6. Flight International 11 July 1968, p. 55.
  7. Apostolo 1984, p. 103.

Bibliography[edit | edit source]

External links[edit | edit source]

  • Westland Widgeon pages at helis.com database

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