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162:<!-- 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> -->
164:|ref= |type= |length= |diameter= |weight= |compressor= |combustion= |turbine= |fueltype= |oilsystem= |power= |thrust= |compression= |bypass= |aircon= |turbinetemp= |fuelcon= |specfuelcon= |power/weight= |thrust/weight= }}
275:|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.
285:|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)
369:|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)
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This template provides formatted output for jet engine (including all turbojets, turbofans, turboprops, and turboshafts) specifications per
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in grams per kilonewton-s — g/(kN·s); and pounds per pounds force-hour — lb/(lbf·h). Use the convert template with the parameters
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The parameters should be entered in the units provided by the reference, converted as needed using the
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should also be wiki-linked). At the very least specify if it is an axial or a centrifugal compressor.
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232:|weight= Dry weight of the engine (without oil, coolant, etc.), in kilograms (kg) and pounds (lb)
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304:|turbinetemp= Turbine inlet temperature, in degrees Celsius (°C) and degrees Fahrenheit (°F)
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lbf thrust divided by lb weight is also dimensionless. To convert a 'weight' given in
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before editing the template. If your edit causes unexpected problems, please
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is defined as a dimensionless quantity. It is calculated by dividing engine
278:|power= Power (for turboshaft and turboprop engines), in kilowatts (kW) and
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You can conduct experiments, and should test all major changes, in either
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to place the most appropriate system of units first when needed, and
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10 flow combustion chambers with igniter plugs in chambers 3 and 10
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it quickly, as this template may appear on a large number of pages.
226:|length= Length of the engine, in millimetres (mm) and inches (in)
253:|combustion= Description of the combustion chambers, for example
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301:|aircon= Air consumption, in kilograms/second and pounds/second
307:|fuelcon= Fuel consumption, in litres/hour and US gallons/hour
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You are encouraged to familiarise yourself with its setup and
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This template employs intricate features of template syntax.
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Knowledge (XXG):WikiProject
Aircraft/Engines/page content
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322:to convert between the two different units. E.g.,
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328:Module:Convert/documentation/conversion_data#Speed
259:|turbine= Description of the turbine, for example
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326:→ 20 lb/(lbf⋅h) (570 g/(kN⋅s)). See
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265:|fueltype= Fuel type, for example
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477:Aircraft specs templates
237:single-stage dual-entry
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271:with 1% lubricating oil
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17:General characteristics
450:Add categories to the
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290:Overall pressure ratio
239:centrifugal compressor
75:Template documentation
413:Template:Jetspecs/doc
198:appropriate precision
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472:Intricate templates
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38:Dry weight:
466:Categories
403:The above
344:by engine
216:turboshaft
196:to ensure
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363: m/s
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267:aviation
220:turboprop
33:Diameter:
374:See also
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212:turbojet
208:turbofan
194:sigfig=N
175:SI units
156:jetspecs
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342:newtons
320:si tsfc
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28:Length:
448:pages.
444:create
436:mirror
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346:weight
338:thrust
222:engine
188:. Use
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147:Usage
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