Thrust-To-Weight Ratio (TWR) Of Jet And Rocket Engines

Thrust-to-weight ratio is a dimensionless ratio of thrust to weight of a rocket, jet engine, propeller engine, or a vehicle propelled by such an engine that indicates the performance of the engine or vehicle.

The instantaneous thrust-to-weight ratio of a vehicle varies continually during operation due to progressive consumption of fuel or propellant and in some cases a gravity gradient.

The thrust-to-weight ratio based on initial thrust and weight is often published and used as a figure of merit for quantitative comparison of the initial performance of vehicles.

Jet Or Rocket Engine	Mass (N)	Thrust (N)	Thrust-To-Weight Ratio (Low To High)
RD-0410 nuclear rocket engine	20,000	35,200	1.8:1
Pratt & Whitney F119	18,000	91,000	5.1:1
Rolls-Royce/Snecma Olympus 593 turbojet with reheat (Concorde)	31,750	169,200	5.3:1
J58 jet engine (SR-71 Blackbird)	27,220	150,000	5.5:1
RD-0750 rocket engine, three-propellant mode	46,210	1,413,000	30.6:1
RD-0146 rocket engine	2,600	98,000	37.7:1
SSME rocket engine (Space Shuttle)	31,770	2,278,000	71.7:1
RD-180 rocket engine	53,930	4,152,000	77.0:1
RD-170 rocket engine	97,500	7,887,000	80.9:1
F-1 (Saturn V first stage)	83,910	7,740,500	92.2:1
NK-33 rocket engine	12,220	1,638,000	134.0:1
Merlin 1D rocket engine	4,400	690,000	156.8:1

http://en.wikipedia.org/wiki/Thrust-to-weight_ratio