Fairchild J44
| J44 | |
|---|---|
| Script error: No such module "InfoboxImage". | |
| A Fairchild J44R-24 on display at the Frontiers of Flight Museum |
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
- Ryan AQM-34 Firebee (B/C)
- Fairchild AQM-41 Petrel
- Bell Model 65
- Fairchild C-123 Provider
- Fairchild C-82 Packet
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, Template:Cvt.
- 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, Template:Cvt.
- J44-R-12
- expendable.
- J44-R-20B
- Ryan Firebee.
- J44-R-24
- Fairchild Petrel.
- J44-R-26
- Template:Cvt 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: Script error: No such module "convert".
- Diameter: Script error: No such module "convert".
- Dry weight: Script error: No such module "convert". 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: Script error: No such module "convert". static thrust at 15,780 rpm
- Overall pressure ratio: 2.7:1
- Air mass flow: Template:Cvt at 15,780 rpm
- Specific fuel consumption: Script error: No such module "convert".
- Thrust-to-weight ratio: 2.9
See also
Related development
Related lists
References
<templatestyles src="Reflist/styles.css" />
Script error: No such module "Check for unknown parameters".
Further reading
Script error: No such module "Side box".
- Script error: No such module "citation/CS1".
Script error: No such module "Navbox". Script error: No such module "Navbox".