قالب:Jetspecs

 المواصفات العامة

• النوع:
• الطول:
• القطر:
• الوزن الجاف:

 المكونات

• الضاغط:

 الآداء

• Maximum power output:
• معدل الطاقة-الوزن:

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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:

 Usage

{{jetspecs
<!-- 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> -->
|ref=
|type=
|length=
|diameter=
|weight=
|compressor=
|combustion=
|turbine=
|fueltype=
|oilsystem=
|power=
|thrust=
|compression=
|bypass=
|aircon=
|turbinetemp=
|fuelcon=
|specfuelcon=
|power/weight=
|thrust/weight=
}}

 Explanation of template parameters

All parameters should be written in both imperial units and metric units. For American and British designs, the format is imperial (metric). For all others, it is metric (imperial).

• |type= Engine in a nutshell, afterburning turbofan/turbojet/turboshaft/turboprop engine
• |length= Length of the engine, in (mm)
• |diameter= Diameter or width of the engine, in (mm)
• |weight= Dry weight of the engine (without oil, coolant, etc.), lb (kg)
• |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, US gal (L) capacity, oil circulation rate US gal/hr (L/hr), maximum inverted flying time, etc.
• |power= Power (for gas-turbine engines), shp (kW)
• |thrust= Thrust, lbf (kN) at # rpm, specify if afterburning or non-afterburning.
• |compression= Overall pressure ratio, #:1
• |bypass= Bypass ratio
• |aircon= Air consumption, lb/s (kg/s)
• |turbinetemp= Turbine inlet temperature, °F (°C)
• |fuelcon= Fuel consumption, US gal/hr (L/hr) or lb/hr (kg/hr)
• |specfuelcon= Specific fuel consumption lb/(lbf·h) (kg/(kN·h))
• |thrust/weight= Thrust-to-weight ratio, calculated by dividing engine thrust by engine weight, lbf thrust divided by lb weight is unitless. Metric kN/kg is the same except multiplied by 9.8.
• |Power/weight= Power-to-weight ratio (for gas-turbine engines), calculated by dividing engine power by engine weight, shp/lb (kW/kg)

 See also

• {{Pistonspecs}}