Specific thrust is a term used in gas turbine

Gas turbine

A gas turbine, also called a combustion turbine, is a type of internal combustion engine. It has an upstream rotating compressor coupled to a downstream turbine, and a combustion chamber in-between....

 engineering

Engineering

Engineering is the discipline, art, skill and profession of acquiring and applying scientific, mathematical, economic, social, and practical knowledge, in order to design and build structures, machines, devices, systems, materials and processes that safely realize improvements to the lives of...

 to show the relative bulk of a jet engine

Jet engine

A jet engine is a reaction engine that discharges a fast moving jet to generate thrust by jet propulsion and in accordance with Newton's laws of motion. This broad definition of jet engines includes turbojets, turbofans, rockets, ramjets, pulse jets...

 (e.g. turbojet, turbofan

Turbofan

The turbofan is a type of airbreathing jet engine that is widely used for aircraft propulsion. A turbofan combines two types of engines, the turbo portion which is a conventional gas turbine engine, and the fan, a propeller-like ducted fan...

, etc) and is defined as the ratio: net thrust/total intake airflow.

Low specific thrust engines

A modern civil turbofan has a low specific thrust (~30 lbf/(lb/s)) to keep the jet noise at an acceptable level, and to achieve low fuel consumption, as a low specific thrust helps to improve specific fuel consumption

Specific fuel consumption

Thrust specific fuel consumption or sometimes simply specific fuel consumption, SFC, is an engineering term that is used to describe the fuel efficiency of an engine design with respect to thrust output...

 (SFC). This low specific thrust is usually achieved with a high bypass ratio

Bypass ratio

The term bypass ratio relates to the design of turbofan engines, commonly used in aviation. It is defined as the ratio between the mass flow rate of air drawn in by the fan bypassing the engine core to the mass flow rate passing through the engine core....

. Additionally a low specific thrust implies that the engine is relatively large in diameter, for the net thrust it produces. Consequently such aircraft engines are normally located externally, in a separate nacelle or pod, attached to the wing, or the rear fuselage.

High specific thrust engines

On the other hand, a modern military turbofan has a fairly high specific thrust (45-110 lbf/(lb/s)), which keeps the cross-sectional area of the engine low, so that (normally) the engine can be easily accommodated within the fuselage, thus minimizing aircraft drag. A high specific thrust implies a high jet noise level, which is not an important consideration for most military applications.

Maximum airspeed

Specific thrust has significant bearing on thrust lapse rate: the low jet velocity associated with a low specific thrust engine implies that there are large reductions in net thrust with increasing flight velocity, which can only be partially offset by throttle changes at rated conditions (e.g. maximum recommended climb rating).

Supersonic aircraft

Supersonic aircraft require a high specific thrust, since that gives a high exhaust speed—exhaust speed must exceed airspeed to maintain forward flight.

Afterburners

Dry specific thrust has impact upon the performance of afterburning turbofans.

A low (dry) specific thrust engine has a low tailpipe temperature, which means that the temperature rise across the afterburner can be high, giving a good thrust boost in afterburning. Nevertheless, the afterburning specific thrust is still relatively low. The total fuel flow (main combustor plus afterburner) is fixed by the temperature rise from air intake to nozzle and, for a given airflow, changes little with dry specific thrust. Consequently, the low afterburning thrust implies a high afterburning SFC. However, the dry SFC is low.

The situation is completely reversed for a high (dry) specific thrust.

Consequently engine designers must select a level of dry specific thrust that is suitable for the engine application. A compromise may be required.