Thrust-specific fuel consumption

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Thrust-specific fuel consumption (TSFC) is the fuel efficiency of an engine design with respect to thrust output. TSFC may also be thought of as fuel consumption (grams/second) per unit of thrust (newtons, or N), hence thrust-specific. This figure is inversely proportional to specific impulse, which is the amount of thrust produced per unit fuel consumed.

Contents

TSFC or SFC for thrust engines (e.g. turbojets, turbofans, ramjets, rockets, etc.) is the mass of fuel needed to provide the net thrust for a given period e.g. lb/(h·lbf) (pounds of fuel per hour-pound of thrust) or g/(s·kN) (grams of fuel per second-kilonewton). Mass of fuel is used, rather than volume (gallons or litres) for the fuel measure, since it is independent of temperature. [1]

Specific fuel consumption of air-breathing jet engines at their maximum efficiency is more or less proportional to exhaust speed. The fuel consumption per mile or per kilometre is a more appropriate comparison for aircraft that travel at very different speeds.[ not in body ] Power-specific fuel consumption, the thrust-specific fuel consumption divided by speed, can have units of pounds per hour per horsepower.

Significance of SFC

SFC is dependent on engine design, but differences in the SFC between different engines using the same underlying technology tend to be quite small. Increasing overall pressure ratio on jet engines tends to decrease SFC.

In practical applications, other factors are usually highly significant in determining the fuel efficiency of a particular engine design in that particular application. For instance, in aircraft, turbine (jet and turboprop) engines are typically much smaller and lighter than equivalently powerful piston engine designs, both properties reducing the levels of drag on the plane and reducing the amount of power needed to move the aircraft. Therefore, turbines are more efficient for aircraft propulsion than might be indicated by a simplistic look at the table below.

SFC varies with throttle setting, altitude, climate. For jet engines, air flight speed is an important factor too. Air flight speed counteracts the jet's exhaust speed. (In an artificial and extreme case with the aircraft flying exactly at the exhaust speed, one can easily imagine why the jet's net thrust should be near zero.) Moreover, since work is force (i.e., thrust) times distance, mechanical power is force times speed. Thus, although the nominal SFC is a useful measure of fuel efficiency, it should be divided by speed when comparing engines at different speeds.

For example, Concorde cruised at 1354 mph, or 7.15 million feet per hour, with its engines giving an SFC of 1.195 lb/(lbf·h) (see below); this means the engines transferred 5.98 million foot pounds per pound of fuel (17.9 MJ/kg), equivalent to an SFC of 0.50 lb/(lbf·h) for a subsonic aircraft flying at 570 mph, which would be better than even modern engines; the Olympus 593 used in the Concorde was the world's most efficient jet engine. [2] [3] However, Concorde ultimately has a heavier airframe and, due to being supersonic, is less aerodynamically efficient, i.e., the lift to drag ratio is far lower. In general, the total fuel burn of a complete aircraft is of far more importance to the customer.

Units

Specific impulse
(by weight)
Specific impulse
(by mass)
Effective
exhaust velocity
Specific fuel consumption
SI=X seconds=9.8066 X N·s/kg=9.8066 X m/s=101,972 (1/X) g/(kN·s) / {g/(kN·s)=s/m}
Imperial units=X seconds=X lbf·s/lb=32.16 X ft/s=3,600 (1/X) lb/(lbf·h)

Typical values of SFC for thrust engines

Rocket engines in vacuum
ModelTypeFirst
run
Application TSFC Isp (by weight)Isp(by mass)
lb/lbf·hg/kN·ssm/s
Avio P80 solid fuel 2006 Vega stage 1133602802700
Avio Zefiro 23 solid fuel2006 Vega stage 212.52354.7287.52819
Avio Zefiro 9A solid fuel2008 Vega stage 312.20345.4295.22895
Merlin 1D liquid fuel 2013 Falcon 9 123303103000
RD-843 liquid fuel 2012 Vega upper stage11.41323.2315.53094
Kuznetsov NK-33 liquid fuel1970s N-1F, Soyuz-2-1v stage 110.9308331 [4] 3250
NPO Energomash RD-171M liquid fuel1985 Zenit-2M, -3SL, -3SLB, -3F stage 110.73033373300
LE-7A cryogenic 2001 H-IIA, H-IIB stage 18.222334384300
Snecma HM-7B cryogenic1979 Ariane 2, 3, 4, 5 ECA upper stage8.097229.4444.64360
LE-5B-2 cryogenic2009 H-IIA, H-IIB upper stage8.052284474380
Aerojet Rocketdyne RS-25 cryogenic1981 Space Shuttle, SLS stage 17.95225453 [5] 4440
Aerojet Rocketdyne RL-10B-2 cryogenic1998 Delta III, Delta IV, SLS upper stage7.734219.1465.54565
NERVA NRX A6 nuclear 1967869
Jet engines with Reheat, static, sea level
ModelTypeFirst
run
Application TSFC Isp (by weight)Isp(by mass)
lb/lbf·hg/kN·ssm/s
Turbo-Union RB.199 turbofan Tornado 2.5 [6] 70.8144014120
GE F101-GE-102 turbofan1970s B-1B 2.4670146014400
Tumansky R-25-300 turbojet MIG-21bis 2.206 [6] 62.5163216000
GE J85-GE-21 turbojet F-5E/F 2.13 [6] 60.3169016570
GE F110-GE-132 turbofan F-16E/F2.09 [6] 59.2172216890
Honeywell/ITEC F125 turbofan F-CK-1 2.06 [6] 58.4174817140
Snecma M53-P2 turbofan Mirage 2000C/D/N2.05 [6] 58.1175617220
Snecma Atar 09C turbojet Mirage III 2.03 [6] 57.5177017400
Snecma Atar 09K-50 turbojet Mirage IV, 50, F1 1.991 [6] 56.4180817730
GE J79-GE-15 turbojet F-4E/EJ/F/G, RF-4E 1.96555.7183217970
Saturn AL-31F turbofan Su-27/P/K 1.96 [7] 55.5183718010
GE F110-GE-129 turbofan F-16C/D, F-15EX1.9 [6] 53.8189518580
Soloviev D-30F6 turbofan MiG-31, S-37/Su-47 1.863 [6] 52.8193218950
Lyulka AL-21F-3 turbojet Su-17, Su-221.86 [6] 52.7193518980
Klimov RD-33 turbofan1974 MiG-29 1.8552.4194619080
Saturn AL-41F-1S turbofan Su-35S/T-10BM 1.81951.5197919410
Volvo RM12 turbofan1978 Gripen A/B/C/D 1.78 [6] 50.4202219830
GE F404-GE-402 turbofan F/A-18C/D 1.74 [6] 49207020300
Kuznetsov NK-32 turbofan1980 Tu-144LL, Tu-160 1.748210021000
Snecma M88-2 turbofan1989 Rafale 1.66347.11216521230
Eurojet EJ200 turbofan1991 Eurofighter 1.66–1.7347–49 [8] 2080–217020400–21300
Dry jet engines, static, sea level
ModelTypeFirst
run
Application TSFC Isp (by weight)Isp(by mass)
lb/lbf·hg/kN·ssm/s
GE J85-GE-21 turbojet F-5E/F 1.24 [6] 35.1290028500
Snecma Atar 09C turbojet Mirage III 1.01 [6] 28.6356035000
Snecma Atar 09K-50 turbojet Mirage IV, 50, F1 0.981 [6] 27.8367036000
Snecma Atar 08K-50 turbojet Super Étendard 0.971 [6] 27.5371036400
Tumansky R-25-300 turbojet MIG-21bis 0.961 [6] 27.2375036700
Lyulka AL-21F-3 turbojet Su-17, Su-220.8624.4419041100
GE J79-GE-15 turbojet F-4E/EJ/F/G, RF-4E 0.8524.1424041500
Snecma M53-P2 turbofan Mirage 2000C/D/N0.85 [6] 24.1424041500
Volvo RM12 turbofan1978 Gripen A/B/C/D 0.824 [6] 23.3437042800
RR Turbomeca Adour turbofan1999 Jaguar retrofit 0.8123440044000
Honeywell/ITEC F124 turbofan1979 L-159, X-45 0.81 [6] 22.9444043600
Honeywell/ITEC F125 turbofan F-CK-1 0.8 [6] 22.7450044100
PW J52-P-408 turbojet A-4M/N, TA-4KU, EA-6B 0.7922.4456044700
Saturn AL-41F-1S turbofan Su-35S/T-10BM 0.7922.4456044700
Snecma M88-2 turbofan1989 Rafale 0.78222.14460045100
Klimov RD-33 turbofan1974 MiG-29 0.7721.8468045800
RR Pegasus 11-61 turbofan AV-8B+ 0.7621.5474046500
Eurojet EJ200 turbofan1991 Eurofighter 0.74–0.8121–23 [8] 4400–490044000–48000
GE F414-GE-400 turbofan1993 F/A-18E/F 0.724 [9] 20.5497048800
Kuznetsov NK-32 turbofan1980 Tu-144LL, Tu-160 0.72-0.7320–214900–500048000–49000
Soloviev D-30F6 turbofan MiG-31, S-37/Su-47 0.716 [6] 20.3503049300
Snecma Larzac turbofan1972 Alpha Jet 0.71620.3503049300
IHI F3 turbofan1981 Kawasaki T-4 0.719.8514050400
Saturn AL-31F turbofan Su-27 /P/K0.666-0.78 [7] [9] 18.9–22.14620–541045300–53000
RR Spey RB.168 turbofan AMX 0.66 [6] 18.7545053500
GE F110-GE-129 turbofan F-16C/D, F-15 0.64 [9] 18560055000
GE F110-GE-132 turbofan F-16E/F0.64 [9] 18560055000
Turbo-Union RB.199 turbofan Tornado ECR 0.637 [6] 18.0565055400
PW F119-PW-100 turbofan1992 F-22 0.61 [9] 17.3590057900
Turbo-Union RB.199 turbofan Tornado 0.598 [6] 16.9602059000
GE F101-GE-102 turbofan1970s B-1B 0.56215.9641062800
PW TF33-P-3 turbofan B-52H, NB-52H 0.52 [6] 14.7692067900
RR AE 3007H turbofan RQ-4, MQ-4C 0.39 [6] 11.0920091000
GE F118-GE-100 turbofan1980s B-2 0.375 [6] 10.6960094000
GE F118-GE-101 turbofan1980s U-2S 0.375 [6] 10.6960094000
General Electric CF6-50C2 turbofan A300, DC-10-300.371 [6] 10.5970095000
GE TF34-GE-100 turbofan A-10 0.37 [6] 10.5970095000
CFM CFM56-2B1 turbofan C-135, RC-135 0.36 [10] 101000098000
Progress D-18T turbofan1980 An-124, An-225 0.3459.810400102000
PW F117-PW-100 turbofan C-17 0.34 [11] 9.610600104000
PW PW2040 turbofan Boeing 757 0.33 [11] 9.310900107000
CFM CFM56-3C1 turbofan 737 Classic 0.339.311000110000
GE CF6-80C2 turbofan 744, 767, MD-11, A300/310, C-5M 0.307-0.3448.7–9.710500–11700103000–115000
EA GP7270 turbofan A380-8610.299 [9] 8.512000118000
GE GE90-85B turbofan 777-200/200ER/3000.298 [9] 8.4412080118500
GE GE90-94B turbofan 777-200/200ER/3000.2974 [9] 8.4212100118700
RR Trent 970-84 turbofan2003 A380-8410.295 [9] 8.3612200119700
GE GEnx-1B70 turbofan 787-8 0.2845 [9] 8.0612650124100
RR Trent 1000C turbofan2006 787-9 0.273 [9] 7.713200129000
Jet engines, cruise
ModelTypeFirst
run
Application TSFC Isp (by weight)Isp(by mass)
lb/lbf·hg/kN·ssm/s
Ramjet Mach 14.51308007800
J-58 turbojet1958 SR-71 at Mach 3.2 (Reheat)1.9 [6] 53.8189518580
RR/Snecma Olympus turbojet1966 Concorde at Mach 21.195 [12] 33.8301029500
PW JT8D-9 turbofan 737 Original 0.8 [13] 22.7450044100
Honeywell ALF502R-5 GTF BAe 146 0.72 [11] 20.4500049000
Soloviev D-30KP-2 turbofan Il-76, Il-78 0.71520.3503049400
Soloviev D-30KU-154 turbofan Tu-154M 0.70520.0511050100
RR Tay RB.183 turbofan1984 Fokker 70, Fokker 100 0.6919.5522051200
GE CF34-3 turbofan1982 Challenger, CRJ100/200 0.6919.5522051200
GE CF34-8E turbofan E170/175 0.6819.3529051900
Honeywell TFE731-60 GTF Falcon 900 0.679 [14] 19.2530052000
CFM CFM56-2C1 turbofan DC-8 Super 70 0.671 [11] 19.0537052600
GE CF34-8C turbofan CRJ700/900/1000 0.67-0.6819–195300–540052000–53000
CFM CFM56-3C1 turbofan 737 Classic 0.66718.9540052900
CFM CFM56-2A2 turbofan1974 E-3, E-6 0.66 [10] 18.7545053500
RR BR725 turbofan2008 G650/ER 0.65718.6548053700
CFM CFM56-2B1 turbofan C-135, RC-135 0.65 [10] 18.4554054300
GE CF34-10A turbofan ARJ21 0.6518.4554054300
CFE CFE738-1-1B turbofan1990 Falcon 2000 0.645 [11] 18.3558054700
RR BR710 turbofan1995 G. V/G550, Global Express 0.6418560055000
GE CF34-10E turbofan E190/195 0.6418560055000
General Electric CF6-50C2 turbofan A300B2/B4/C4/F4, DC-10-300.63 [11] 17.8571056000
PowerJet SaM146 turbofan Superjet LR 0.62917.8572056100
CFM CFM56-7B24 turbofan 737 NG 0.627 [11] 17.8574056300
RR BR715 turbofan1997 717 0.6217.6581056900
GE CF6-80C2-B1F turbofan 747-400 0.605 [12] 17.1595058400
CFM CFM56-5A1 turbofan A320 0.59616.9604059200
Aviadvigatel PS-90A1 turbofan Il-96-4000.59516.9605059300
PW PW2040 turbofan 757-2000.582 [11] 16.5619060700
PW PW4098 turbofan 777-300 0.581 [11] 16.5620060800
GE CF6-80C2-B2 turbofan 767 0.576 [11] 16.3625061300
IAE V2525-D5 turbofan MD-90 0.574 [15] 16.3627061500
IAE V2533-A5 turbofan A321-231 0.574 [15] 16.3627061500
RR Trent 700 turbofan1992 A330 0.562 [16] 15.9641062800
RR Trent 800 turbofan1993 777-200/200ER/300 0.560 [16] 15.9643063000
Progress D-18T turbofan1980 An-124, An-225 0.54615.5659064700
CFM CFM56-5B4 turbofan A320-214 0.54515.4661064800
CFM CFM56-5C2 turbofan A340-211 0.54515.4661064800
RR Trent 500 turbofan1999 A340-500/600 0.542 [16] 15.4664065100
CFM LEAP-1B turbofan2014 737 MAX 0.53-0.5615–166400–680063000–67000
Aviadvigatel PD-14 turbofan2014 MC-21-310 0.52614.9684067100
RR Trent 900 turbofan2003 A380 0.522 [16] 14.8690067600
GE GE90-85B turbofan 777-200/200ER 0.52 [11] [17] 14.7692067900
GE GEnx-1B76 turbofan2006 787-10 0.512 [13] 14.5703069000
PW PW1400G GTF MC-21 0.51 [18] 14.4710069000
CFM LEAP-1C turbofan2013 C919 0.5114.4710069000
CFM LEAP-1A turbofan2013 A320neo family 0.51 [18] 14.4710069000
RR Trent 7000 turbofan2015 A330neo 0.506 [a] 14.3711069800
RR Trent 1000 turbofan2006 787 0.506 [b] 14.3711069800
RR Trent XWB-97 turbofan2014 A350-1000 0.478 [c] 13.5753073900
PW 1127G GTF2012 A320neo 0.463 [13] 13.1778076300
Civil engines [19]
ModelSL thrustBPROPR SL SFCcruise SFCWeightLayoutcost ($M)Introduction
GE GE90 90,000 lbf
400 kN
8.439.30.545 lb/(lbf⋅h)
15.4 g/(kN⋅s)
16,644 lb
7,550 kg
1+3LP 10HP
2HP 6LP
111995
RR Trent 71,100–91,300 lbf
316–406 kN
4.89-5.7436.84-42.70.557–0.565 lb/(lbf⋅h)
15.8–16.0 g/(kN⋅s)
10,550–13,133 lb
4,785–5,957 kg
1LP 8IP 6HP
1HP 1IP 4/5LP
11-11.71995
PW4000 52,000–84,000 lbf
230–370 kN
4.85-6.4127.5-34.20.348–0.359 lb/(lbf⋅h)
9.9–10.2 g/(kN⋅s)
9,400–14,350 lb
4,260–6,510 kg
1+4-6LP 11HP
2HP 4-7LP
6.15-9.441986-1994
RB211 43,100–60,600 lbf
192–270 kN
4.3025.8-330.570–0.598 lb/(lbf⋅h)
16.1–16.9 g/(kN⋅s)
7,264–9,670 lb
3,295–4,386 kg
1LP 6/7IP 6HP
1HP 1IP 3LP
5.3-6.81984-1989
GE CF6 52,500–67,500 lbf
234–300 kN
4.66-5.3127.1-32.40.32–0.35 lb/(lbf⋅h)
9.1–9.9 g/(kN⋅s)
0.562–0.623 lb/(lbf⋅h)
15.9–17.6 g/(kN⋅s)
8,496–10,726 lb
3,854–4,865 kg
1+3/4LP 14HP
2HP 4/5LP
5.9-71981-1987
D-18 51,660 lbf
229.8 kN
5.6025.00.570 lb/(lbf⋅h)
16.1 g/(kN⋅s)
9,039 lb
4,100 kg
1LP 7IP 7HP
1HP 1IP 4LP
1982
PW2000 38,250 lbf
170.1 kN
631.80.33 lb/(lbf⋅h)
9.3 g/(kN⋅s)
0.582 lb/(lbf⋅h)
16.5 g/(kN⋅s)
7,160 lb
3,250 kg
1+4LP 11HP
2HP 5LP
41983
PS-90 35,275 lbf
156.91 kN
4.6035.50.595 lb/(lbf⋅h)
16.9 g/(kN⋅s)
6,503 lb
2,950 kg
1+2LP 13HP
2 HP 4LP
1992
IAE V2500 22,000–33,000 lbf
98–147 kN
4.60-5.4024.9-33.400.34–0.37 lb/(lbf⋅h)
9.6–10.5 g/(kN⋅s)
0.574–0.581 lb/(lbf⋅h)
16.3–16.5 g/(kN⋅s)
5,210–5,252 lb
2,363–2,382 kg
1+4LP 10HP
2HP 5LP
1989-1994
CFM56 20,600–31,200 lbf
92–139 kN
4.80-6.4025.70-31.500.32–0.36 lb/(lbf⋅h)
9.1–10.2 g/(kN⋅s)
0.545–0.667 lb/(lbf⋅h)
15.4–18.9 g/(kN⋅s)
4,301–5,700 lb
1,951–2,585 kg
1+3/4LP 9HP
1HP 4/5LP
3.20-4.551986-1997
D-30 23,850 lbf
106.1 kN
2.420.700 lb/(lbf⋅h)
19.8 g/(kN⋅s)
5,110 lb
2,320 kg
1+3LP 11HP
2HP 4LP
1982
JT8D 21,700 lbf
97 kN
1.7719.20.519 lb/(lbf⋅h)
14.7 g/(kN⋅s)
0.737 lb/(lbf⋅h)
20.9 g/(kN⋅s)
4,515 lb
2,048 kg
1+6LP 7HP
1HP 3LP
2.991986
BR700 14,845–19,883 lbf
66.03–88.44 kN
4.00-4.7025.7-32.10.370–0.390 lb/(lbf⋅h)
10.5–11.0 g/(kN⋅s)
0.620–0.640 lb/(lbf⋅h)
17.6–18.1 g/(kN⋅s)
3,520–4,545 lb
1,597–2,062 kg
1+1/2LP 10HP
2HP 2/3LP
1996
D-436 16,865 lbf
75.02 kN
4.9525.20.610 lb/(lbf⋅h)
17.3 g/(kN⋅s)
3,197 lb
1,450 kg
1+1L 6I 7HP
1HP 1IP 3LP
1996
RR Tay 13,850–15,400 lbf
61.6–68.5 kN
3.04-3.0715.8-16.60.43–0.45 lb/(lbf⋅h)
12–13 g/(kN⋅s)
0.690 lb/(lbf⋅h)
19.5 g/(kN⋅s)
2,951–3,380 lb
1,339–1,533 kg
1+3LP 12HP
2HP 3LP
2.61988-1992
RR Spey 9,900–11,400 lbf
44–51 kN
0.64-0.7115.5-18.40.56 lb/(lbf⋅h)
16 g/(kN⋅s)
0.800 lb/(lbf⋅h)
22.7 g/(kN⋅s)
2,287–2,483 lb
1,037–1,126 kg
4/5LP 12HP
2HP 2LP
1968-1969
GE CF34 9,220 lbf
41.0 kN
210.35 lb/(lbf⋅h)
9.9 g/(kN⋅s)
1,670 lb
760 kg
1F 14HP
2HP 4LP
1996
AE3007 7,150 lbf
31.8 kN
24.00.390 lb/(lbf⋅h)
11.0 g/(kN⋅s)
1,581 lb
717 kg
ALF502/LF5076,970–7,000 lbf
31.0–31.1 kN
5.60-5.7012.2-13.80.406–0.408 lb/(lbf⋅h)
11.5–11.6 g/(kN⋅s)
0.414–0.720 lb/(lbf⋅h)
11.7–20.4 g/(kN⋅s)
1,336–1,385 lb
606–628 kg
1+2L 7+1HP
2HP 2LP
1.661982-1991
CFE738 5,918 lbf
26.32 kN
5.3023.00.369 lb/(lbf⋅h)
10.5 g/(kN⋅s)
0.645 lb/(lbf⋅h)
18.3 g/(kN⋅s)
1,325 lb
601 kg
1+5LP+1CF
2HP 3LP
1992
PW300 5,266 lbf
23.42 kN
4.5023.00.391 lb/(lbf⋅h)
11.1 g/(kN⋅s)
0.675 lb/(lbf⋅h)
19.1 g/(kN⋅s)
993 lb
450 kg
1+4LP+1HP
2HP 3LP
1990
JT15D 3,045 lbf
13.54 kN
3.3013.10.560 lb/(lbf⋅h)
15.9 g/(kN⋅s)
0.541 lb/(lbf⋅h)
15.3 g/(kN⋅s)
632 lb
287 kg
1+1LP+1CF
1HP 2LP
1983
WI FJ44-4A 1,900 lbf
8.5 kN
3.2812.800.456 lb/(lbf⋅h)
12.9 g/(kN⋅s)
0.75 lb/(lbf⋅h)
21 g/(kN⋅s)
445 lb
202 kg
1+1L 1C 1H
1HP 2LP
1992
WI FJ33-5A 1,000–1,800 lbf
4.4–8.0 kN
0.486 lb/(lbf⋅h)
13.8 g/(kN⋅s)
300 lb
140 kg
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

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).

typical subsonic cruise, 80% throttle, min SFC [20]
Turbofanefficiency
GE90 36.1%
PW4000 34.8%
PW2037 35.1% (M.87 40K)
PW2037 33.5% (M.80 35K)
CFM56-230.5%
TFE731-223.4%

See also

Notes

  1. 10% better than Trent 700
  2. 10% better than Trent 700
  3. 15 per cent fuel consumption advantage over the original Trent engine

References

  1. Specific Fuel Consumption.
  2. Supersonic Dream
  3. "The turbofan engine Archived 2015-04-18 at the Wayback Machine ", page 5. SRM Institute of Science and Technology, Department of aerospace engineering
  4. "NK33". Encyclopedia Astronautica.
  5. "SSME". Encyclopedia Astronautica.
  6. 1 2 3 4 5 6 7 8 9 10 11 12 13 14 15 16 17 18 19 20 21 22 23 24 25 26 27 28 29 30 31 32 33 Nathan Meier (21 Mar 2005). "Military Turbojet/Turbofan Specifications". Archived from the original on 11 February 2021.
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