F404 / F412
An F404 turbofan being tested on board an aircraft carrier
Type	Turbofan
National origin	United States
Manufacturer	General Electric
First run	1978
Major applications	Boeing–Saab T-7 Red Hawk HAL Tejas Mk 1/1A KAI T-50 Golden Eagle Lockheed F-117 Nighthawk McDonnell Douglas F/A-18 Hornet Northrop F-20 Tigershark TAI Hurjet
Developed from	General Electric YJ101
Variants	Volvo RM12
Developed into	General Electric F414 General Electric GE36 General Electric LM1600

The General Electric F404 and F412 are a family of afterburning turbofan engines in the 10,500–19,000 lbf (47–85 kN) class (static thrust). The series is produced by GE Aerospace. Partners include Volvo Aero, which builds the RM12 variant. The F404 was developed into the larger F414 turbofan, as well as the experimental GE36 civil propfan.

GE developed the F404 for the F/A-18 Hornet, shortly after losing the competition for the F-15 Eagle's engine to Pratt & Whitney, and losing the Lightweight Fighter (LWF) competition to the Pratt & Whitney F100 powered YF-16. For the F/A-18, GE based the F404 on the YJ101 engine they had developed for the Northrop YF-17, enlarging the bypass ratio from 0.20 to 0.34 to enable higher fuel efficiency. The engine consists of a three-staged fan, seven axial stage compressor arrangement, single stage low and high pressure turbines, an afterburner, and produces maximum thrust of 16,000 lbf (71.2 kN) in the original F404-GE-400 model. The engine was designed with a higher priority on reliability than performance. Cost was the main goal in the design of the engine.^[1]

GE also analyzed "throttle profiles" and found that pilots were changing throttle settings far more often than engineers previously expected, putting undue stress on the engines. GE also sought with the F404 a design that would avoid compressor stalls and other engine failures, and would respond quickly to control inputs; a common complaint of pilots converting from propeller planes to jets was that early turbojets were not responsive to changes in thrust input. GE executives Frederick A. Larson and Paul Setts also set the goal that the new engine would be smaller than the F-4's GE J79, but provide at least as much thrust, and cost half as much as the P&W F100 engine for the F-16.^[2]

Due to a fan designed to smooth airflow before it enters the compressor, the F404 has high resistance to compressor stalls, even at high angles of attack. It requires less than two shop visits per 1,000 flight hours and averages 6,500 hours between in-flight events. It also demonstrates high responsiveness to control inputs, spooling from idle to full afterburner in 4 seconds. The engine contains an in-flight engine condition monitoring system (IECMS) that monitors for critical malfunctions and keeps track of parts lifetimes.^[3]

GE developed the F110 for the Air Force as an alternative to the Pratt & Whitney F100 for use on the F-16 and F-15 based on the F101 and used F404 technology.^[4] The F110 was derived from the F101 via the F101DFE, though some elements of the F404 such as the design of the fan, albeit enlarged, were incorporated, per the F110 page and other sources. GE developed the F404-GE-402 in response to a Swiss requirement for more power in its F/A-18 version; it produces a maximum of 17,700 lbf (78.7 kN) of thrust with afterburner.^[5] The new engine version was used on Kuwaiti Hornets, later U.S. C and D Hornets, and subsequent Hornets.^[5] The KAI T-50 Golden Eagle uses a single General Electric F404-GE-102 turbofan engine with Full Authority Digital Engine Control (FADEC) system; the engine is similar to the F404-402, but with additional redundancies built in for single-engine operations. The aircraft has a maximum speed of Mach 1.5.

Almost 4,000 F404 engines power the F/A-18 Hornets in service worldwide. The F404 engine family had totaled over 12 million flight hours by 2010.^[6]

For HAL Tejas, GE developed an uprated F404-IN20, which is the highest thrust variant in F404 family, and which produces a maximum of 19,000 lbf (85 kN) of thrust with afterburner.^[7][8] It incorporates latest hot section materials and technologies as well as FADEC system for reliable power and performance.^[9] India bought 10 F404-F2J3 which is used on 2 technology Demonstrators and 6 prototypes of Tejas in early 2000s.^[10] Two deals for 17 and 24 engines for powering LSP (including Naval prototypes) and Mk 1 IOC variants of Tejas was signed in 2004 and 2007, respectively.^[11][8] As of September 2024, 75 engines (including F2J3 and IN20 variants) have been delivered to India.^[12] On 17 August 2021, India signed a contract with GE worth ₹5,375 crore (equivalent to ₹60 billion or US$720 million in 2023) to supply 99 F404 engines and service support by 2029.^[9][13] However, the first engine of the deal signed in 2021 is yet to be delivered as of July 2024 which has led to the delay of delivery of HAL Tejas Mk1A aircraft to the Indian Air Force. Afterwards, reports suggested that engine delivery is expected to commence from September 2024 at the rate of 1-2 per month.^[14][15] On 5 September 2024, it was reported that 2 F404-IN20 engines are scheduled to be shipped in September followed by 6 more by the end of fiscal year.^[16]

GE developed the F404 into the F412-GE-400 non-afterburning turbofan for the McDonnell Douglas A-12 Avenger II. After the cancellation of the A-12, the research was directed toward an engine for the Super Hornet, which evolved into the F414.

F404

• Boeing Phantom Ray
• Boeing X-45C
• Boeing–Saab T-7 Red Hawk
• FMA SAIA 90 (as designed, not built)
• Dassault Rafale A (prototype only)
• Grumman A-6F Intruder II
• Grumman X-29
• HAL Tejas Mk 1/1A
• Lockheed F-117 Nighthawk
• KAI T-50 Golden Eagle
• McDonnell Douglas F/A-18 Hornet (A-D)
• Northrop F-20 Tigershark
• Scaled Composites Model 400
• Rockwell-MBB X-31
• ST Aerospace A-4SU Super Skyhawk
• TAI Hürjet

F412

• McDonnell Douglas A-12 Avenger II (as designed, not built)

Data from General Electric^[17]

• Type: afterburning turbofan
• Length: 154 in (391 cm)
• Diameter: 35 in (89 cm) overall, 28 in (71 cm) inlet
• Dry weight: 2,282 lb (1,035 kg)

• Compressor: axial, with 3 fan and 7 HP stages
• Combustors: annular
• Turbine: 1 LP and 1 HP stage

• Maximum thrust:
  
  • 11,000 lbf (48.9 kN) military thrust
  • 17,700 lbf (78.7 kN) with afterburner
• Overall pressure ratio: 26:1
• Bypass ratio: 0.34:1
• Air mass flow: 146 lb/s (66.2 kg/s)
• Specific fuel consumption:
  
  • Military thrust: 0.81 lb/(lbf⋅h) (23 g/(kN⋅s))
  • Full afterburner: 1.74 lb/(lbf⋅h) (49 g/(kN⋅s))
• Thrust-to-weight ratio: 4.8 (dry), 7.75 (afterburning)

Related development

• General Electric YJ101
• General Electric F414
• General Electric F110
• Volvo RM12

Comparable engines

• GTRE GTX-35VS Kaveri
• Guizhou WS-13
• Klimov RD-33
• Snecma M88
• Turbo-Union RB199

Related lists

• List of aircraft engines

• Jenkins, Dennis R. F/A-18 Hornet: A Navy Success Story. New York: McGraw-Hill, 2000. ISBN 0-07-134696-1.

Wikimedia Commons has media related to General Electric F404.

• GE Aviation F404 page
• F404 page on GlobalSecurity.org