Fairchild J83

The J83 turbojet was developed starting in 1955 to power cruise missiles used as un-armed decoys for bomber aircraft. The J83 development was terminated in November 1958.

History

In March 1953, the United States Air Force released General Operaional Requirement (GOR)16 which called air and ground launched decoy missiles to increase the effectiveness of Strategic Air Command bombers by confusing and saturating a air defense system. In December 1955, Fairchild was awarded a contract to develop the ground-launched decoy Weapon System 123A which included the XSM-73 Goose missile. McDonnell Aircraft was chosen in February 1956 to build the ADM-20 Quail air-launched decoy.

Two engine contracts were awarded in November 1954 to minimize development risk for both decoys. Each engine was in the 2,450 lb. (10.9 kN) thrust class with a thrust to weight ratio goal of 10:1. General Electric was awarded a contract for the development of the General Electric J85 and Fairchild was awarded a contract for a competing engine the J83.Fairchild proposed a lightweight engine of conventional design. General Electric used a more advanced design which yielded a higher thrust to weight ratio.

A J83 was operating by early 1957. A B-57 Canberra was modified and used as a flying engine testbed for the J-83. The J83 powered the XSM-73 Goose on 15 test flights.

Fairchild competed with two other engine manufacturers to provide the power-plant for the Canadair
Canadair CL-41 Tutor. A license built General Electric J85 was chosen. The Northrop XQ-4A, was developed to use the J83 engine, but when the engine could not be developed in time the Northrop XQ-4A was canceled.

In November 1958, the J83 was canceled one month before the XSM-73. The USAF determined that the General Electric J85 had a higher probability of meeting the desired performance goals. The General Electric J85 could also be used to power the ADM-20 Quail decoy, the XSM-73 Goose, and the T-38 Talon. The J83 could only be used to power the XSM-73 Goose.

After the J83 was canceled, FairchildEngine Division had no other applications for the engine as result operations at the Fairchild Engine Division plant at Deer ParkLong Island ended in the summer of 1959.

Specifications

jetspecs

type=turbojet
length=
diameter=
weight= 363 lb. (165 kg.)
compressor=seven stage transonic axial flow compressor
combustion=annular combuster
turbine=two-stage turbine
fueltype=JP-4
oilsystem=
power=
thrust=2,450 lb. (10.9 kN)
compression=
aircon=
turbinetemp=
fuelcon=
specfuelcon=0.94 SFC
power/weight=
thrust/weight=6.5:1

Applications

* YJ83-R-1
** XSM-73 Goose
* J83-R-1
** Northrop XQ-4A (Never Built)

References

* "The History of North American Small Gas Turbine Aircraft Engines", William Fleming and Richard Leyes, AIAA, 1999