Thrust-to-weight ratio

Thrust-to-weight ratio is a ratio of thrust to weight of a rocket, jet engine, propeller engine, or a vehicle propelled by such an engine. It is a dimensionless quantity and is an indicator of 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 due to 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.

Calculation

The thrust-to-weight ratio can be calculated by dividing the thrust (in SI units – in newtons) by the weight (in newtons) of the engine or vehicle. It is a dimensionless quantity.

For valid comparison of the initial thrust-to-weight ratio of two or more engines or vehicles, thrust must be measured under controlled conditions.

Aircraft

The thrust-to-weight ratio and wing loading are the two most important parameters in determining the performance of an aircraft. For example, the thrust-to-weight ratio of a combat aircraft is a good indicator of the manoeuvrability of the aircraft.

The thrust-to-weight ratio varies continually during a flight. Thrust varies with throttle setting, airspeed, altitude and air temperature. Weight varies with fuel burn and changes of payload. For aircraft, the quoted thrust-to-weight ratio is often the maximum static thrust at sea-level divided by the maximum takeoff weight.

In cruising flight, the thrust-to-weight ratio of an aircraft is the inverse of the lift-to-drag ratio because thrust is equal to drag, and weight is equal to lift.

$\left (\frac{T}{W}\right)_{cruise}=\frac{1}{(\frac{L}{D})_{cruise}}$

Propeller-driven aircraft

For propeller-driven aircraft, the thrust-to-weight ratio can be calculated as follows:

$\frac{T}{W}=\left(\frac{\eta_p}{V}\right)\left(\frac{P}{W}\right)$

where $\eta_p\;$ is propulsive efficiency at true airspeed $V\;$

$P\;$ is engine power

Rockets

Rocket vehicle Thrust-to-weight ratio vs Isp for different propellant technologies.

The thrust-to-weight ratio of a rocket, or rocket-propelled vehicle, is an indicator of its acceleration expressed in multiples of gravitational acceleration g.

Rockets and rocket-propelled vehicles operate in a wide range of gravitational environments, including the weightless environment. It is customary to calculate the thrust-to-weight ratio using initial gross weight at sea-level on earth. This is sometimes called Thrust-to-Earth-weight ratio. 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, g₀.

It is important to note that the thrust-to-weight ratio for a rocket varies as the propellant gets utilized. If the thrust is constant, then the maximum ratio (maximum acceleration of the vehicle) is achieved just before the propellant is fully consumed (propellant weight is practically zero at this point). So for each rocket there a characteristic thrust-to-weight curve or acceleration curve, not just a scalar quantity.

The thrust-to-weight ratio of an engine is larger for the bare engine than for the whole launch vehicle. The thrust-to-weight ratio of a bare engine is of use since it determines the maximum acceleration that any vehicle using that engine could theoretically achieve with minimum propellant and structure attached.

For a takeoff from the surface of the earth using thrust and no aerodynamic lift, the thrust-to-weight ratio for the whole vehicle has to be more than one. In general, the thrust-to-weight ratio is numerically equal to the g-force that the vehicle can generate. Provided the vehicle's g-force exceeds local gravity (expressed as a multiple of g₀) then takeoff can occur.

The thrust to weight ratio of rockets is typically far higher than that of airbreathing jet engines. This is because of the much higher density of the material that is formed into the exhaust, compared to that of air; therefore, far less engineering materials are needed for pressurising it.

Many factors affect a thrust-to-weight ratio, and the instantaneous value typically varies over the flight with the variations of thrust due to speed and altitude, and the weight due to the remaining propellant and payload mass. The main factors that affect thrust include freestream air temperature, pressure, density, and composition. Depending on the engine or vehicle under consideration, the actual performance will often be affected by buoyancy and local gravitational field strength.

Examples

The Russian-made RD-180 rocket engine (which powers Lockheed Martin’s Atlas V) produces 3,820 kN of sea-level thrust and has a dry mass of 5,307 kg.^{[citation needed]} Using the Earth surface gravitational field strength of 9.807 m/s², the sea-level thrust-to-weight ratio is computed as follows: (1 kN = 1000 N = 1000 kg⋅m/s²)

$\frac{T}{W}=\frac{3,820\ \mathrm{kN}}{(5,307\ \mathrm{kg})(9.807\ \mathrm{m/s^2})}=0.07340\ \frac{\mathrm{kN}}{\mathrm{N}}=73.40\ \frac{\mathrm{N}}{\mathrm{N}}=73.40$

Aircraft

Vehicle	T/W	Scenario
Concorde	0.373[citation needed]	Max Takeoff Weight, Full Reheat
English Electric Lightning	0.63[citation needed]	maximum takeoff weight, No Reheat
F-22 Raptor	>1.09 (1.26 with loaded weight & 50% fuel)	Maximum takeoff weight, Dry Thrust
Mikoyan MiG-29	1.09	Full internal fuel, 4 AAMs
F-15 Eagle	1.04	nominally loaded
F-16 Fighting Falcon	1.096[citation needed]
Hawker Siddeley Harrier	1.1[citation needed]
English Electric Lightning	~1.2	on an empty weight basis, full reheat
Eurofighter Typhoon	1.07 (100% fuel, 2 IRIS-T, 4 MBDA Meteor)
Space Shuttle	1.5	Take-off
Dassault Rafale	0.988 (100% fuel, 2 EM A2A missile, 2 IR A2A missile) version M
Space Shuttle	3	Peak (throttled back for astronaut comfort)

Jet and Rocket Engines

Jet or Rocket engine	Mass (kg)	Mass (lb)	Thrust (kN)	Thrust (lbf)	Thrust-to-weight ratio
RD-0410 nuclear rocket engine	2,000	4,400	35.2	7,900	1.8
J58 jet engine (SR-71 Blackbird)	2,722	6,000	150	34,000	5.2
Rolls-Royce/Snecma Olympus 593 turbojet with reheat (Concorde)	3,175	7,000	169.2	38,000	5.4
Pratt & Whitney F119	1,800	3,900	91	20,500	7.95
RD-0750 rocket engine, three-propellant mode	4,621	10,190	1,413	318,000	31.2
RD-0146 rocket engine	260	570	98	22,000	38.4
SSME rocket engine (Space Shuttle)	3,177	7,000	2,278	512,000	73.1
RD-180 rocket engine	5,393	11,890	4,152	933,000	78.5
F-1 (Saturn V first stage)	8,391	18,500	7,740.5	1,740,100	94.1
NK-33 rocket engine	1,222	2,690	1,638	368,000	136.7
Merlin 1D rocket engine	440	970	690	160,000	159.9

Rocket thrusts are vacuum thrusts unless otherwise noted

Fighter Aircraft

Table a: Thrust To Weight Ratios, Fuels Weights, and Weights of Different Fighter Planes

Specifications / Fighters	F-15K	F-15C	MiG-29K	MiG-29B	JF-17	J-10	F-35A	F-35B	F-35C	F-22
Engine(s) Thrust Maximum (lbf)	58,320 (2)	46,900 (2)	39,682 (2)	36,600 (2)	18,300 (1)	27,557 (1)	39,900 (1)	39,900 (1)	39,900 (1)	70,000 (2)
Aircraft Weight Empty (lb)	37,500	31,700	28,050	24,030	14,520	20,394	29,300	32,000	34,800	43,340
Aircraft Weight Full fuel (lb)	51,023	45,574	39,602	31,757	19,650	28,760	47,780	46,003	53,800	61,340
Aircraft Weight Max Take-off load (lb)	81,000	68,000	49,383	40,785	28,000	42,500	70,000	60,000	70,000	83,500
Total fuel weight (lb)	13,523	13,874	11,552	07,727	05,130	08,366	18,480	14,003	19,000	18,000
T/W ratio (Thrust / AC weight full fuel)	1.14	1.03	1.00	1.15	0.93	0.96	0.84	0.87	0.74	1.14

Table b: Thrust To Weight Ratios, Fuels Weights, and Weights of Different Fighter Planes (In International System)

In International System	F-15K	F-15C	MiG-29K	MiG-29B	JF-17	J-10	F-35A	F-35B	F-35C	F-22
Engine(s) Thrust Maximum (kgf)	26,456 (2)	21,274 (2)	18,000 (2)	16,600 (2)	08,300 (1)	12,500 (1)	18,098 (1)	18,098 (1)	18 098 (1)	31,764 (2)
Aircraft Weight Empty (kg)	17,010	14,379	12,723	10,900	06,586	09,250	13,290	14,515	15,785	19,673
Aircraft Weight Full fuel (kg)	23,143	20,671	17,963	14,405	08,886	13,044	21,672	20,867	24,403	27,836
Aircraft Weight Max Take-off load (kg)	36,741	30,845	22,400	18,500	12,700	19,277	31,752	27,216	31,752	37,869
Total fuel weight (kg)	06,133	06,292	05,240	03,505	02,300	03,794	08,382	06,352	08,618	08,163
T/W ratio (Thrust / AC weight full fuel)	1.14	1.03	1.00	1.15	0.93	0.96	0.84	0.87	0.74	1.14

• Fuel density used in calculations = 0.803 Kilograms/Liter
• The Number inside ( ) brackets is the Number of Engine(s).
• Engines powering F-15K are the Pratt & Whitney Engines, not General Electric's.
• MiG-29K's empty weight is an estimate.
• JF-17's Engine rating is of RD-93.
• JF-17 if mated with its engine WS-13, and if that engine gets its promised 18,969 lb then the T/W ratio becomes 0.97
• J-10's empty weight & fuel weight is an estimate.
• J-10's Engine rating is of AL-31FN.
• J-10 if mated with its engine WS-10A, and if that engine gets its promised 132 KN(29,674 lbf) then the T/W ratio becomes 1.03

See also

• Power-to-weight ratio
• Factor of safety

References

• John P. Fielding. Introduction to Aircraft Design, Cambridge University Press, ISBN 978-0-521-65722-8
• Daniel P. Raymer (1989). Aircraft Design: A Conceptual Approach, American Institute of Aeronautics and Astronautics, Inc., Washington, DC. ISBN 0-930403-51-7
• George P. Sutton & Oscar Biblarz. Rocket Propulsion Elements, Wiley, ISBN 978-0-471-32642-7

External links

• NASA webpage with overview and explanatory diagram of aircraft thrust to weight ratio