|CA25-39 Winjeel A85-439 at the RAAF Museum|
|Manufacturer||Commonwealth Aircraft Corporation|
|First flight||23 February 1955|
|Status||Some examples now privately owned or in museums|
|Primary user||Royal Australian Air Force|
|Number built||2 (CA-22)
Design and development
The Winjeel was developed by the Commonwealth Aircraft Corporation at Fishermans Bend in Victoria to satisy RAAF technical requirement No.AC.77. Sixty two aircraft were built and given the fleet serials A85-401 to A85-462.
The first Winjeel entered service with No.1 Basic Flight Training School (BFTS) at Uranquinty, near Wagga Wagga, New South Wales. For most of the service life of the Winjeel it was used as a basic-training aircraft at RAAF Base Point Cook in Victoria. The Winjeel remained in service with the RAAF as a basic-training aircraft until replaced by the New Zealand-built PAC CT/4A in 1977.
A small number of Winjeels were used in the Forward Air Control (FAC) role from 1977 until 1994. By then there were fourteen examples in service with No. 76 Squadron, and that year they were replaced by the Pilatus PC-9. Examples of the aircraft remain in flying condition in private ownership as well as museum displays around Australia.
- CA-22 Winjeel : Prototypes. Only two aircraft were built.
- CA-25 Winjeel : Two-seat basic trainer aircraft for the RAAF. 62 aircraft were built.
Data from Jane's All The World's Aircraft 1955–56
- Crew: 2
- Capacity: Two seats side by side under rearwards sliding canopy with provision for a third seat in rear of cabin
- Length: 29 ft 01⁄2 in (8.55 m)
- Wingspan: 38 ft 71⁄2 in (11.77 m)
- Height: 9 ft 1 in (2.77 m)
- Wing area: 249 sq ft (23.1 m2)
- Airfoil: NACA 23015 at root, NACA 23010 at tip
- Aspect ratio: 6.0:1
- Empty weight: 3,289 lb (1,495 kg)
- Loaded weight: 4,265 lb (1,939 kg)
- Powerplant: 1 × Pratt & Whitney R-985-AN-2 Wasp Junior nine cylinder radial engine, 445 hp (332 kW)
- Maximum speed: 186 mph (162 knots, 291 km/h)
- Cruise speed: 165 mph (143 knots, 265 km/h)
- Stall speed: 53 mph (46 knots, 85 km/hr) (flaps down)
- Endurance: 3.5 hours at 158 mph (137 kn; 254 km/h)
- Service ceiling: 18,000 ft (5,490 m)
- Rate of climb: 1,500 ft/min (7.6 m/s)
- Take-off run to 50 ft (15 m): 1,110 ft (340 m) (standard temperature)
- Landing run from 50 ft (15 m): 1,000 ft (305 m)
- Aircraft of comparable role, configuration and era
- Related lists
- Bridgman, Leonard (1955). Jane's All The World's Aircraft 1955–56. New York: The McGraw Hill Book Company.
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