Revision as of 17:48, 5 October 2019 by Ozycaevias (talk | contribs) (1 revision imported)

General characteristics

  • Type:
  • Length:
  • Diameter:
  • Dry weight:


  • Compressor:


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This template provides formatted output for jet engine (including all turbojets, turbofans, turboprops, and turboshafts) specifications per Wikipedia:WikiProject Aircraft/Engines/page content. To use this template, copy-paste the following text:


<!-- If you do not understand how to use this template, please ask at [[Wikipedia talk:WikiProject Aircraft]] -->
<!-- Please include units where appropriate (main comes first, alt in parentheses). If data are missing, leave the parameter blank (do not delete it). For additional lines, end your alt units with )</li> and start a new, fully formatted line with <li> -->

Explanation of template parameters

All parameters should be written in both SI units (metric) and imperial/US customary units.

The parameters should be entered in the units provided by the reference, converted as needed using the convert template. Use order=flip to place the most appropriate system of units first when needed, and sigfig=N to ensure appropriate precision when needed.

  • |type= Engine in a nutshell, afterburning turbofan/turbojet/turboshaft/turboprop engine
  • |length= Length of the engine, in millimetres (mm) and inches (in)
  • |diameter= Diameter or width of the engine, in millimetres and inches
  • |weight= Dry weight of the engine (without oil, coolant, etc.), in kilograms (kg) and pounds (lb)
  • |compressor= Description of the compressor (number of stages, high/low pressure stages, number of blades, etc.), for example single-stage dual-entry centrifugal compressor with two-sided impeller (axial compressor should also be wiki-linked). At the very least specify if it is an axial or a centrifugal compressor.
  • |combustion= Description of the combustion chambers, for example 10 flow combustion chambers with igniter plugs in chambers 3 and 10
  • |turbine= Description of the turbine, for example single-stage axial flow with 54 blades
  • |fueltype= Fuel type, for example aviation kerosene with 1% lubricating oil
  • |oilsystem= Description of the oil system. E.g., capacity in litres and US gallons, oil circulation rate in litres/hour (l/h) and US gallons/hour (US gal/h), maximum inverted flying time, etc.
  • |power= Power (for turboshaft and turboprop engines), in kilowatts (kW) and shaft horsepower (shp)
  • |thrust= Thrust, in kilonewtons (kN) and pounds-force (lbf) at specified number of revolutions per minute (rpm), specify if afterburning or non-afterburning and provide both if appropriate)
  • |compression= Overall pressure ratio, #:1
  • |bypass= Bypass ratio
  • |aircon= Air consumption, in kilograms/second and pounds/second
  • |turbinetemp= Turbine inlet temperature, in degrees Celsius (°C) and degrees Fahrenheit (°F)
  • |fuelcon= Fuel consumption, in litres/hour and US gallons/hour
  • |specfuelcon= Thrust specific fuel consumption in grams per kilonewton-s — g/(kN·s); and pounds per pounds force-hour — lb/(lbf·h). Use the convert template with the parameters tsfc and si tsfc to convert between the two different units. E.g., {{convert|20|tsfc|si tsfc}}→ 20 lb/(lbf⋅h) (570 g/(kN⋅s)). See Module:Convert/documentation/conversion_data#Speed
  • |thrust/weight= Thrust to weight ratio is defined as a dimensionless quantity. It is calculated by dividing engine thrust in newtons by engine weight in newtons. US customary units lbf thrust divided by lb weight is also dimensionless. To convert a 'weight' given in kilograms into a weight in newtons, multiply by 9.80665 m/s2.
  • |Power/weight= Power-to-weight ratio (for gas-turbine engines), calculated by dividing engine power by engine weight, kilowatts/kilogram (kW/kg) and shaft horsepower/pound (shp/lb)

See also