Template:Jetspecs/doc

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

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.,  → 20 tsfc. See Module:Convert/documentation/conversion_data
 * 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 $9.807 m/s2$.
 * 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)