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The thrust-to-Earth-weight ratio of a rocket or rocket-propelled vehicle is an indicator of its acceleration expressed in multiples of earth's gravitational acceleration, g 0. [5] The thrust-to-weight ratio of a rocket improves as the propellant is burned. With constant thrust, the maximum ratio (maximum acceleration of the vehicle) is achieved ...
The ATF's increasing weight during development required more thrust to meet the performance requirements; as gross weight grew to 60,000 lb (27,200 kg), the required maximum thrust was increased by 20% to 35,000 lbf (156 kN) class. Pratt & Whitney's design changed to incorporate a 15% larger fan, increasing bypass ratio from 0.25 to 0.30.
Data from China Aerospace Propulsion Technology Forum 2022 General characteristics Type: afterburning turbofan Length: Diameter: Dry weight: Components Compressor: axial Combustors: annular Performance Maximum thrust: 26,000 lbf (116 kN; 11,793 kgf) with afterburner Thrust-to-weight ratio: ~10 See also Xian WS-15 Comparable engines General Electric F414 Eurojet EJ200 Snecma M88-3 Related lists ...
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]
The initial F100-PW-100 variant generates nearly 24,000 lbf (107 kN) of thrust in full afterburner and weighs approximately 3,000 lb (1,361 kg), achieving its target thrust-to-weight ratio of 8 and providing the F-15 with its desired thrust-to-weight ratio of greater than 1:1 at combat weight.
Each engine has dual-redundant Hamilton Standard full-authority digital engine control and maximum thrust in the 35,000 lbf (156 kN) class. The F-22's thrust-to-weight ratio at typical combat weight is nearly at unity in maximum military power and 1.25 in full afterburner.
It has a thrust-to-weight ratio greater than one, providing power to climb and vertical acceleration. [67] The F-16 was designed to be relatively inexpensive to build and simpler to maintain than earlier-generation fighters. The airframe is built with about 80% aviation-grade aluminum alloys, 8% steel, 3% composites, and 1.5% titanium.
Max takeoff weight: 51,900 lb (23,541 kg) Fuel capacity: 10,860 pounds (4,930 kg) internally Powerplant: 2 × General Electric F404-GE-402 afterburning turbofan engines, 11,000 lbf (49 kN) thrust each dry, 17,750 lbf (79.0 kN) with afterburner