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With the TF30, the F-14's overall thrust-to-weight ratio at maximum takeoff weight is around 0.56, considerably less than the F-15A's ratio of 0.85; when fitted with the F110 engine, an improved thrust-to-weight ratio of 0.73 at maximum weight and 0.88 at normal takeoff weight was achieved. [52]
thrust-weight ratio Notes Northrop Grumman B-2 Spirit: 0.205 [8] Max take-off weight, full power Airbus A340: 0.2229 Max take-off weight, full power (A340-300 Enhanced) Airbus A380: 0.227 Max take-off weight, full power Boeing 747-8: 0.269 Max take-off weight, full power Boeing 777: 0.285 Max take-off weight, full power (777-200ER) Boeing 737 ...
Power cycle Specific impulse (s) [a] Thrust (N) [a] Chamber pressure (bar) Mass (kg) Thrust: weight ratio [e] Oxidiser: fuel ratio Aeon 1
The power-to-weight ratio (specific power) is defined as the power generated by the engine(s) divided by the mass. In this context, the term "weight" can be considered a misnomer, as it colloquially refers to mass. In a zero-gravity (weightless) environment, the power-to-weight ratio would not be considered infinite.
The Grumman F-14 Tomcat with the TF30-P-414A was underpowered, because it was the Navy's intent to procure a jet fighter with a thrust-to-weight ratio (in clean configuration) of 1 or better (the US Air Force had the same goals for the F-15 Eagle and F-16 Fighting Falcon).
The General Electric F110 is an afterburning turbofan jet engine produced by GE Aerospace (formerly GE Aviation). It was derived from the General Electric F101 as an alternative engine to the Pratt & Whitney F100 for powering tactical fighter aircraft, with the F-16C Fighting Falcon and F-14A+/B Tomcat being the initial platforms; the F110 would eventually power new F-15 Eagle variants as well.
The Pratt & Whitney F401 (company designation JTF22 [1]) was an afterburning turbofan engine developed by Pratt & Whitney in tandem with the company's F100.The F401 was intended to power the Grumman F-14 Tomcat and Rockwell XFV-12, but the engine was canceled due to costs and development issues.
Vehicle Liftoff Mass Payload Mass to LEO Mass ratio Payload fraction Falcon 9 Block 5: 549,054 kg + 22,800 kg 22,800 kg 25.1 3.99% Proton-M: 705,000 kg + 23,000 kg