Difference between revisions of "Template:Jetspecs/doc"
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imported>Michael F 1967 m (→Explanation of template parameters: Corrected a really stupid mistake I made.) |
imported>Michael F 1967 (→Explanation of template parameters: Changed in line with discussion at Wikipedia_talk:WikiProject_Aircraft/Engines#Template:Jetspecs_-_units_of_measurement.) |
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==Explanation of template parameters== | ==Explanation of template parameters== | ||
| − | All parameters should be written in both [[ | + | All parameters should be written in both [[International_System_of_Units#Units_and_prefixes|SI units]] (metric) and [[Imperial_and_US_customary_measurement_systems#Units_in_use|imperial/US customary units]]. |
| + | |||
| + | The parameters should be entered in the units provided by the reference, converted as needed using the [[Help:Convert|convert template]]. Use [[Help:Convert#Flipping_the_order_of_output|order=flip]] to place the most appropriate system of units first when needed, and [[Help:Convert#Rounding|sigfig=N]] to ensure [[Significant_figures|appropriate precision]] when needed. | ||
*|type= Engine in a nutshell, ''afterburning [[turbofan]]/[[turbojet]]/[[turboshaft]]/[[turboprop]] engine'' | *|type= Engine in a nutshell, ''afterburning [[turbofan]]/[[turbojet]]/[[turboshaft]]/[[turboprop]] engine'' | ||
Revision as of 17:34, 1 September 2019
| This is a documentation subpage for Template:Jetspecs. It contains usage information, categories and other content that is not part of the original template page. |
| This template employs intricate features of template syntax.
You are encouraged to familiarise yourself with its setup and parser functions before editing the template. If your edit causes unexpected problems, please undo it quickly, as this template may appear on a large number of pages. You can conduct experiments, and should test all major changes, in either this template's sandbox, the general template sandbox, or your user space before changing anything here. |
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 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 (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/h (L/h), 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/h (L/h) or lb/h (kg/h)
- |specfuelcon= Specific fuel consumption lb/(lbf·h) (kg/(kN·h))
- |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 [[standard gravity|Template:Val]].
- |Power/weight= Power-to-weight ratio (for gas-turbine engines), calculated by dividing engine power by engine weight, shp/lb (kW/kg)
See also
- {{Electricspecs}}
- {{Pistonspecs}}