en Fairchild J44

J44
	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

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

Variants

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)

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

References

^ 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.

Fairchild J44