Editing Thrust-specific fuel consumption (section)

==Typical values of SFC for thrust engines==
{{Thrust engine efficiency}}

{| class="wikitable sortable mw-collapsible mw-collapsed"
! colspan="10" |Civil engines<ref>{{cite web |author=Lloyd R. Jenkinson |display-authors=etal |date=30 Jul 1999 |title=Civil Jet Aircraft Design: Engine Data File |url=https://booksite.elsevier.com/9780340741528/appendices/data-b/table-3/default.htm |publisher=Elsevier/Butterworth-Heinemann}}</ref>
|-
! Model !! data-sort-type="number" | SL thrust !! data-sort-type="number" | {{abbr|BPR|Bypass ratio}} !! data-sort-type="number" | {{abbr|OPR|Overall Pressure ratio}}
! data-sort-type="number" | [[Sea level|SL]] SFC !! data-sort-type="number" | cruise SFC !! data-sort-type="number" | Weight
! Layout !! data-sort-type="number" |cost ($M) !! data-sort-type="date" | Introduction
|-
| [[GE GE90]] || {{cvt|90000|lbf|kN|disp=br}} || 8.4 || 39.3
| || {{cvt|0.545|tsfc|si tsfc|disp=br}} || {{cvt|16644|lb|kg|disp=br}}
| 1+3LP 10HP<br/>2HP 6LP || 11 || 1995
|-
| [[RR Trent]] ||	{{cvt|71100-91300|lbf|kN|disp=br}}	 ||	4.89-5.74 ||	36.84-42.7
|		 || {{cvt|0.557-0.565|tsfc|si tsfc|disp=br}} ||	{{cvt|10550-13133|lb|kg|disp=br}}
|	1LP 8IP 6HP<br/>1HP 1IP 4/5LP ||	11-11.7	 || 1995
|-
| [[PW4000]] || {{cvt|52000-84000|lbf|kN|disp=br}} || 4.85-6.41 || 27.5-34.2 
| {{cvt|0.348-0.359|tsfc|si tsfc|disp=br}} || || {{cvt|9400-14350|lb|kg|disp=br}}
| 1+4-6LP 11HP<br/>2HP 4-7LP || 6.15-9.44 || 1986-1994
|-
| [[RB211]] ||	{{cvt|43100-60600|lbf|kN|disp=br}} ||	4.30 ||	25.8-33
|	 ||	{{cvt|0.570-0.598|tsfc|si tsfc|disp=br}} ||	{{cvt|7264-9670|lb|kg|disp=br}}
|	1LP 6/7IP 6HP<br/>1HP 1IP 3LP ||	5.3-6.8  || 1984-1989
|-
| [[GE CF6]] || {{cvt|52500-67500|lbf|kN|disp=br}} || 4.66-5.31 ||	27.1-32.4
| {{cvt|0.32-0.35|tsfc|si tsfc|disp=br}} || {{cvt|0.562-0.623|tsfc|si tsfc|disp=br}} || {{cvt|8496-10726|lb|kg|disp=br}}
| 1+3/4LP 14HP<br/>2HP 4/5LP || 5.9-7 || 1981-1987	
|-
| [[Progress D-18T|D-18]]	||	{{cvt|51660|lbf|kN|disp=br}}	||	5.60	||	25.0	
|	||		{{cvt|0.570|tsfc|si tsfc|disp=br}}	||	{{cvt|9039|lb|kg|disp=br}}
|	1LP 7IP 7HP<br/>1HP 1IP 4LP	||	||		1982
|-
| [[PW2000]] || {{cvt|38250|lbf|kN|disp=br}} || 6 || 31.8
| {{cvt|0.33|tsfc|si tsfc|disp=br}} || {{cvt|0.582|tsfc|si tsfc|disp=br}} || {{cvt|7160|lb|kg|disp=br}}
| 1+4LP 11HP<br/>2HP 5LP || 4 || 1983
|-
| [[PS-90]]	||	{{cvt|35275|lbf|kN|disp=br}}	||	4.60	||	35.5	
|	||		{{cvt|0.595|tsfc|si tsfc|disp=br}}	||	{{cvt|6503|lb|kg|disp=br}}
|	1+2LP 13HP<br/>2 HP 4LP	||	||		1992
|-
| [[IAE V2500]] || {{cvt|22000-33000|lbf|kN|disp=br}} || 4.60-5.40 || 24.9-33.40
| {{cvt|0.34-0.37|tsfc|si tsfc|disp=br}} || {{cvt|0.574-0.581|tsfc|si tsfc|disp=br}} || {{cvt|5210-5252|lb|kg|disp=br}}
| 1+4LP 10HP<br/>2HP 5LP || || 1989-1994
|-
| [[CFM56]] || {{cvt|20600-31200|lbf|kN|disp=br}} || 4.80-6.40 || 25.70-31.50
| {{cvt|0.32-0.36|tsfc|si tsfc|disp=br}} || {{cvt|0.545-0.667|tsfc|si tsfc|disp=br}} || {{cvt|4301-5700|lb|kg|disp=br}}
| 1+3/4LP 9HP<br/>1HP 4/5LP || 3.20-4.55 || 1986-1997
|-
| [[Soloviev D-30|D-30]]	||	{{cvt|23850|lbf|kN|disp=br}}	||	2.42	||	
|	||		{{cvt|0.700|tsfc|si tsfc|disp=br}}	||	{{cvt|5110|lb|kg|disp=br}}
|	1+3LP 11HP<br/>2HP 4LP	||	||		1982
|-
| [[JT8D]] || {{cvt|21700|lbf|kN|disp=br}} || 1.77 ||	19.2
| {{cvt|0.519|tsfc|si tsfc|disp=br}} || {{cvt|0.737|tsfc|si tsfc|disp=br}} || {{cvt|4515|lb|kg|disp=br}}
| 1+6LP 7HP<br/>1HP 3LP || 2.99 || 1986
|-
| [[BR700]]	||	{{cvt|14845-19883|lbf|kN|disp=br}}	|| 4.00-4.70	||	25.7-32.1	
|	{{cvt|0.370-0.390|tsfc|si tsfc|disp=br}}	||	{{cvt|0.620-0.640|tsfc|si tsfc|disp=br}}	||	{{cvt|3520-4545|lb|kg|disp=br}}
|	1+1/2LP 10HP<br/>2HP 2/3LP	||	||		1996
|-
| [[Progress D-436|D-436]]	||	{{cvt|16865|lbf|kN|disp=br}}	||	4.95	||	25.2	
|	||		{{cvt|0.610|tsfc|si tsfc|disp=br}}	||	{{cvt|3197|lb|kg|disp=br}}
|	1+1L 6I 7HP<br/>1HP 1IP 3LP	||	||		1996
|-
| [[Rolls-Royce RB.183 Tay|RR Tay]]	||	{{cvt|13850-15400|lbf|kN|disp=br}}	||	3.04-3.07	||	15.8-16.6
|	{{cvt|0.43-0.45|tsfc|si tsfc|disp=br}}	||	{{cvt|0.690|tsfc|si tsfc|disp=br}}	||	{{cvt|2951-3380|lb|kg|disp=br}}
|	1+3LP 12HP<br/>2HP 3LP	||	2.6	|| 1988-1992
|-
| [[Rolls-Royce Spey|RR Spey]] ||	{{cvt|9900-11400|lbf|kN|disp=br}} ||	0.64-0.71 ||	15.5-18.4
|	{{cvt|0.56|tsfc|si tsfc|disp=br}} ||	{{cvt|0.800|tsfc|si tsfc|disp=br}} ||	{{cvt|2287-2483|lb|kg|disp=br}}
|	4/5LP 12HP<br/>2HP 2LP ||		 || 1968-1969
|-
| [[GE CF34]] || {{cvt|9220|lbf|kN|disp=br}} || ||21
| {{cvt|0.35|tsfc|si tsfc|disp=br}} || || {{cvt|1670|lb|kg|disp=br}}
| 1F 14HP<br/>2HP 4LP ||  || 1996
|-
| [[AE3007]]	||	{{cvt|7150|lbf|kN|disp=br}}	||			||24.0	
|	{{cvt|0.390|tsfc|si tsfc|disp=br}}	||	||		{{cvt|1581|lb|kg|disp=br}}
|	||	||				
|-
| [[ALF502]]/LF507	||	{{cvt|6970-7000|lbf|kN|disp=br}}	||	5.60-5.70	||	12.2-13.8	
|	{{cvt|0.406-0.408|tsfc|si tsfc|disp=br}}	||	{{cvt|0.414-0.720|tsfc|si tsfc|disp=br}}	||	{{cvt|1336-1385|lb|kg|disp=br}}
| 1+2L 7+1HP<br/>2HP 2LP	|| 1.66 ||		1982-1991
|-
| [[CFE738]]	||	{{cvt|5918|lbf|kN|disp=br}}	||	5.30	||	23.0	
|	{{cvt|0.369|tsfc|si tsfc|disp=br}}	||	{{cvt|0.645|tsfc|si tsfc|disp=br}}	||	{{cvt|1325|lb|kg|disp=br}}
|	1+5LP+1CF<br/>2HP 3LP	||	||		1992
|-
| [[PW300]]	||	{{cvt|5266|lbf|kN|disp=br}}	||	4.50	||	23.0	
|	{{cvt|0.391|tsfc|si tsfc|disp=br}}	||	{{cvt|0.675|tsfc|si tsfc|disp=br}}	||	{{cvt|993|lb|kg|disp=br}}
|	1+4LP+1HP<br/>2HP 3LP	||	||	1990
|-
| [[JT15D]]	||	{{cvt|3045|lbf|kN|disp=br}}	||	3.30	||	13.1	
|	{{cvt|0.560|tsfc|si tsfc|disp=br}}	||	{{cvt|0.541|tsfc|si tsfc|disp=br}}	||	{{cvt|632|lb|kg|disp=br}}
|	1+1LP+1CF<br/>1HP 2LP	||	||		1983
|-
| [[Williams FJ44|WI FJ44-4A]] ||	{{cvt|1900|lbf|kN|disp=br}}	||		3.28||		12.80
|	{{cvt|0.456|tsfc|si tsfc|disp=br}}	||	{{cvt|0.75|tsfc|si tsfc|disp=br}}	||	{{cvt|445|lb|kg|disp=br}}
|	1+1L 1C 1H<br/>1HP 2LP	||	||		1992
|-
|[[Williams FJ33|WI FJ33-5A]]
|{{cvt|1000-1800|lbf|kN|disp=br}}
|
|
|{{cvt|0.486|tsfc|si tsfc|disp=br}}
|
|{{cvt|300|lb|kg|disp=br}}
|
|
|2016
|}

The following table gives the efficiency for several engines when running at 80% throttle, which is approximately what is used in cruising, giving a minimum SFC. The efficiency is the amount of power propelling the plane divided by the rate of [[energy consumption]]. Since the power equals thrust times speed, the efficiency is given by
:<math>\eta=V/(SFC\times h)</math>
where V is speed and h is the energy content per unit mass of fuel (the [[higher heating value]] is used here, and at higher speeds the kinetic energy of the fuel or propellant becomes substantial and must be included). 

{| class="wikitable sortable"
|+ typical subsonic cruise, 80% throttle, min SFC<ref>{{cite web |url= http://adg.stanford.edu/aa241/propulsion/sfc.html |title= Specific Fuel Consumption and Overall Efficiency |work= Aircraft Design: Synthesis and Analysis |author= Ilan Kroo |publisher= Stanford University|archive-url=https://web.archive.org/web/20161124123017/http://adg.stanford.edu/aa241/propulsion/sfc.html|archive-date=November 24, 2016}}</ref>
|-
! Turbofan !! efficiency
|-
| [[GE90]] || 36.1%
|-
| [[PW4000]] || 34.8%
|-
| [[PW2000|PW2037]] || 35.1% (M.87 40K)
|-
| [[PW2000|PW2037]] || 33.5% (M.80 35K)
|-
| [[CFM56]]-2 || 30.5%
|-
| [[TFE731]]-2 || 23.4%
|}