|Major applications||AGM-136 Tacit Rainbow|
Development and Design
The F121 engine had a rare set of design parameters as it is designed to be used only once. As a cruise missile engine, it was designed to have a long shelf life (be able to sit around unused for long periods of time) and then operate when needed for several hours. It was designed to power the AGM-136 Tacit Rainbow, which was to be a stand-off anti radiation missile. Its first flight was on July 30, 1984. The AGM-136 program was canceled several years later.
Another unique feature of the engine is that it was started with an explosive cartridge because it couldn't start while still mated to its aircraft.
- Type: Single Spool Turbofan
- Length: 40 in (1.01 m)
- Diameter: 8.5 in (0.22 m)
- Dry weight: 49 lb (22.22 kg)
- Compressor: 1 stage axial fan, 6-stage axial compressor
- Combustors: Turbomeca Piméné-type
- Turbine: 2-stage axial
- Maximum thrust: 70 lbf (0.31 kN)
- Bypass ratio: 1.7:1
- Air mass flow: 5 lb/s (approx)
- Thrust-to-weight ratio: 1.43:1
|Wikimedia Commons has media related to Williams F121.|
- Leyes, p. 421
- Williams International F-121 Fanjet. National Museum of the US Air Force Fact Sheet. Accessed 17 July 2017.
- Kraemer, Nathan A. (2007). Development and Qualification of a Specialized Gas Turbine Test Stand to Research the Potential Benefits of Nanocatalyst Fuel Additives. Master's Thesis, Naval Postgraduate School.
- Leyes II, Richard A.; William A. Fleming (1999). "7". The History of North American Small Gas Turbine Aircraft Engines. Washington, DC: Smithsonian Institution. ISBN 1-56347-332-1.