Fairchild J44
| J44 | |
|---|---|
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| |
| A Fairchild J44R-24 on display at the Frontiers of Flight Museum | |
| Type | Turbojet |
| National origin | United States |
| Manufacturer | Fairchild Engine Division |
| First run | August 1948 |
| Major applications | Ryan AQM-34 Firebee C-123 Provider |
| Developed into | Fairchild J83 |
The Fairchild J44 was a small turbojet developed in the 1940s by the Fairchild Engine Division.
Design and development[edit]
The Fairchild Engine Division (previously the Ranger Aircraft Engine Division of the Fairchild Engine & Aircraft Corporation) began development of the J44 in 1947. It was used in target drones, missiles, and as jet boosters on several aircraft types.
Applications[edit]
- Ryan AQM-34 Firebee (B/C)
- Fairchild AQM-41 Petrel
- Bell Model 65
- Fairchild C-123 Provider
- Fairchild C-82 Packet
Variants[edit]
Data from: Aircraft engines of the World 1953,[1] Flight 20 March 1959 :AERO ENGINES 1959 . . .,[2] Aircraft engines of the World 1957[3]
- XJ44
- Prototypes of the J44
- J44-R-1
- United States Air Force (USAF) engine, similar to the United States Navy (USN) -6, 950 lbf (4.2 kN).
- J44-R-2
- Same as -6 but with different installation.
- J44-R-3
- Longer life - Fairchild C-123 Provider wing-tip boosters.
- J44-R-6
- USN version, 950 lbf (4.2 kN).
- J44-R-12
- expendable.
- J44-R-20B
- Ryan Firebee.
- J44-R-24
- Fairchild Petrel.
- J44-R-26
- 1,100 lbf (4.9 kN) company sponsored variant.
- FT-101E
- Commercial version of -3.
- FT-101-G
- Commercial version with return oil system.
Specifications(J44-R-3)[edit]
Data from Jane's all the World's Aircraft 1955-56,[4] Minijets: Fairchild J44,[5] Turbojet History and Development 1930-1960 Volume 2,[6] Aircraft engines of the World 1957[3]
General characteristics
- Type: turbojet
- Length: 90.4 in (2,300 mm)
- Diameter: 24.3 in (620 mm)
- Dry weight: 370 lb (170 kg) dry, complete
Components
- Compressor: single stage axial/centrifugal flow compressor
- Combustors: annular combustion chamber with 12 burner nozzles
- Turbine: single-stage axial-flow turbine
- Fuel type: JP-4
- Oil system: Oil-mist total loss
Performance
- Maximum thrust: 1,000 lbf (4.45 kN) static thrust at 15,780 rpm
- Overall pressure ratio: 2.7:1
- Air mass flow: 25 lb/s (11 kg/s) at 15,780 rpm
- Specific fuel consumption: 1.55 lb/(lbf⋅h) (44 g/(kN⋅s))
- Thrust-to-weight ratio: 2.9
See also[edit]
Related development
Related lists
References[edit]
- ^ Wilkinson, Paul H. (1953). Aircraft engines of the World 1953 (11th ed.). London: Sir Isaac Pitman & Sons Ltd. p. 46.
- ^ "AERO ENGINES 1959 . . . :Fairchild". Flight. 75 (2617): 404. 20 March 1959. Retrieved 7 January 2019.
- ^ a b Wilkinson, Paul H. (1957). Aircraft engines of the World 1957 (15th ed.). London: Sir Isaac Pitman & Sons Ltd. p. 64.
- ^ Bridgman, Leonard (1955). Jane's all the World's Aircraft 1955-56. London: Jane's all the World's Aircraft Publishing Co. Ltd.
- ^ "Fairchild J44". Minijets (in French). Retrieved 7 January 2019.
- ^ Kay, Anthony L. (2007). Turbojet History and Development 1930-1960 Volume 2:USSR, USA, Japan, France, Canada, Sweden, Switzerland, Italy and Hungary. Vol. 2 (1st ed.). Ramsbury: The Crowood Press. pp. 151–152. ISBN 978-1-86126-939-3.
Further reading[edit]
Wikimedia Commons has media related to Fairchild J44.
- Leyes, Richard II (1999). The History of North American small gas turbine aircraft engines. AIAA. ISBN 978-1-56347-332-6.</ref>