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weight and performance calculations for the Boeing 757-200 (PW2037)
Delta Airlines Boeing 757-231 N723TW c/n 29378 taking off from Los Angeles Int’l apt.(LAX) , October 2013. Later productions 757-200’s had the option to have winglets at the tip of the wings.
Boeing 757-200 (PW2037)
role : jet airliner
importance : ****
first flight : 14 March 1984 operational : November 1984
country : United States of America
ICAO aircraft type designator : B752
production : 757 total : 1050 aircraft, 757-200 : 913
general information :
With the PW 2037 engines, the 757 was no less than 76% more economical than the 727!
From April 1990, EROPS (more usually indicated as ETOPS) flights could be carried out with these engines, i.e. over large areas of water.
On November 12, 1980, Delta ordered no less than 60 aircraft of this version plus an option on another 28. They are fitted with winglets for better aerodynamic performance.
At over 4,000 nautical miles (7,400 km), as of February 2015, the longest commercial route served by a 757 is United Airlines' Newark to Berlin flight; the aircraft assigned to this route cannot fly with full payload. United's 757s assigned to transatlantic routes are fitted with 169 seats. In July 2018, 611 of the 757-200 versions were in service.
primary users : Delta airlines, Northwest airlines, Aeroperu
Accommodation:
flight crew : 2 cabin crew : 6
passengers : seating for 194 in two class : 14 first class and 180 economy class seats
( 32 -in pitch) high density seating for max 239 passengers (equal to exit limit)
engine : 2 Pratt & Whitney PW2037 turbofan engines of 170.0 [KN] (38217 [lbf])
/image1.png)
dimensions :
wingspan : 38.05 [m], length overall: 47.32 [m], length of fuselage : 46.97 [m] height : 13.56 [m]
wing area gross : 185.25 [m^2] fuselage exterior width : 3.76 [m]
weights :
empty weight : 57039 [kg]
operating empty weight : 59364 [kg] max. structural payload : 24097 [kg]
Zero Fuel weight (ZFW) : 83461 [kg] max. landing weight (MLW) : 89811 [kg]
max. take-off weight : 113398 [kg] weight usable fuel : 33507 [kg] (42684 [litres])
performance :
Max. operating Mach number (Mmo) : 0.862 [Mach] (960 [km/hr]) at 7500 [m]
critical Mach speed : 0.78 [Mach]
max. cruising speed : 885 [km/hr] (Mach 0.82 ) at 10000 [m] (33 [%] power)
economic cruising speed : 838 [km/hr] (Mach 0.78 ) at 10000 [m]
service ceiling : 11674 [m]
range with max fuel and MTOW : 7055 [km] (ATA domestic fuel reserves - 370.0 [km] alternate)
description :
*Cantilever low-wing monoplane with retractable landing gear with nose wheel
engines and landing gear attached to the wings, fuel tanks in the wings and fuselage
*Wings : two main spar fail-safe wing structure with double slotted trailing edge flaps with full-span slotted LE flaps (slats) ,with spoilers airfoil : Boeing airfoil with supercritical cross-section. average thickness/chord ratio : 12.7 [%], sweep angle 3/4 chord: 25.0 [°] incidence at root : 3.20 [°], dihedral : 5.0 [°]
*Fuselage : Pressurized conventional all-metal semi-monocoque fail safe structure of circular section
calculation : *1* (dimensions)
wing chord at root : 8.20 [m]
wing chord at tip : 1.73 [m]
taper ratio : 0.211 [ ]
mean wing chord : 4.87 [m]
wing aspect ratio : 7.82 []
Oswald factor (e): 0.699 []
seize (span*length*height) : 24415 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 0.6 [kg/hr]
fuel consumption (econ. cruise speed) : 3781.7 [kg/hr] (4817.4 [litre/hr]) at 22 [%] power
distance flown for 1 kg fuel : 0.22 [km/kg] at 10000 [m] height, sfc : 51.0 [kg/KN/h]
total fuel capacity : 42684 [litre] (33507 [kg])
calculation : *3* (weight)
weight engine(s) dry : 6442.0 [kg] = 18.95 [kg/KN]
weight 14.8 litre oil tank : 1.26 [kg]
oil tank filled with 2.1 litre oil : 1.9 [kg]
oil in engine 4.2 litre oil : 3.7 [kg]
weight all fuel lines and pumps containing 80 litres fuel : 78.6 [kg]
weight engine cowling : 884.0 [kg]
/image2.png)
757-200 N557NW rolling out at RW26 Phoenix airport, November 2005, with extended thrust reversers, deployed spoilers and flaps. Note the two overwing exits. Looks like most airlines choose for the type II emergency exit behind the wing and not for the overwing exits.
.
weight thrust reversers : 510.0 [kg]
total weight propulsion system : 7922 [kg](7.0 [%])
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standard seating is relatively dense, expected seating : 188 [pax]
Accommodation cabin facilities:
/image3.png)
typical 2-class cabin layout for 194 passengers : economy : pitch : 81.3 [cm] 32.0 [-in]
( 3+3 ) seating in 33.5 rows first class pitch : 96.5 [cm] 38.0 [-in] at 4 -abreast
weight passenger seats (width 51.0 [cm]) : 939.4 [kg]
weight cabin crew seats : 30.0 [kg]
weight flight crew seats : 42.0 [kg]
high density seating passengers : 239 [pax] at mainly 6 -abreast seating in 41.2 rows, pitch 78.7 [cm] 31.0 [-in]
pax density, normal seating : 0.659 [m2/pax], high density seating : 0.535 [m2/pax]
weight 4 lavatories : 115.1 [kg]
weight 2 galleys : 205.6 [kg]
/image4.png)
weight overhead stowage for hand luggage (total : 10.1 [m3] = 211 55x35x25cm carry-on trolleys) : 158.1 [kg]
weight 2 wardrobe closets : 52.5 [kg]
weight 3 movie screens : 25.9 [kg]
weight 69 windows (47x38cm) made of acrylic glass: 293.3 [kg]
weight 4 (1.83 x 0.84 [m]) main entry doors : 209.6 [kg]
weight 2 (1.65 x 0.76 [m]) galley service doors : 85.5 [kg]
weight 2 (main door size : 1.14 x 1.40 [m]) freight doors (belly) : 118.3 [kg]*
total usable belly baggage/cargo hold volume : 50.7 [m3]
cabin volume (usable), excluding flight deck : 231 [m3]
passenger compartment volume : 154 [m3]
passenger cabin max width : 3.54 [m] cabin length : 36.09 [m] max cabin height : 2.13 [m]
floor area : 116.0 [m2]
weight cabin facilities : 2275.5 [kg]
safety facilities:
weight 4 type III over wing emergency exits (51x91 cm): 66.9 [kg]
evacuation time with 239 passengers : 45 [sec]
weight 4 hand fire extinguisher : 13 [kg]
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators (deploy cabin alt.>4267m): 126.1 [kg]
weight emergency flare installation : 10 [kg]
weight 6 emergency evacuation slides : 165.8 [kg]
weight safety equipment & facilities : 402 [kg]
/image5.png)
fuselage construction:
fuselage aluminium frame : 12462 [kg]
floor loading (payload/m2): 208 [kg/m2]
weight rear pressure bulkhead : 194.3 [kg]
fuselage covering ( 420.2 [m2] duraluminium 3.32 [mm]) : 3655.6 [kg]
weight paint fuselage : 88.2 [kg]
weight aluminium floor beams : 667.8 [kg]
weight cabin furbishing : 989.2 [kg]
weight cabin floor : 1763.8 [kg]
weight (sound proof) isolation : 312.5 [kg] TO-noise level : 96.0 [EPNdB]
weight 26427 [litre] main central fuel tank empty : 528.5 [kg]
weight empty 328 [litre] potable water tanks : 29.0 [kg]
weight empty waste tank : 13.9 [kg]
weight fuselage structure : 20705.0 [kg]
Avionics:
weight VHF radio and Selcal : 9.0 [kg]
weight flight and service attendants intercom : 5.0 [kg]
weight monochromatic weather X-band (3.2cm wavelength) radar system : 25.0 [kg]
weight VOR/ILS,RMI,DME,radio altimeter, ASI, time clock : 20.0 [kg]
weight dual digital Flight Management System (FMS) for navigation/auto-pilot : 20.0 [kg]
weight Cat IIIA auto-landing system : 10.0 [kg]
weight EFIS (4 Rockwell Collins CRT screens ADI/PFD+HSI/ND displays) : 20 [kg]
weight ground proximity warning system (GPWS) : 6 [kg]
weight 2 Rockwell Collins CRT screens to display EICAS information : 30 [kg]
weight reserve ADI, ASI, alti-meter, compass, engine temp. and rpm indicators : 15 [kg]
weight avionics : 147.0 [kg]
/image6.png)
Dutchbird 757-230 landing at Schiphol airport
Systems:
Air-conditioning and pressurization system maintains sea level conditions up to 7100 [m]
and gives equivalent of 2000 [m] at 12200 [m]. pressure differential : 0.62 [bar] (kg/cm2)
pressurized fuselage volume : 412 [m3] cabin air refreshment time : 2.8 [min]
weight air-conditioning and pressurization system : 251 [kg]
weight APU / engine starter : 85.0 [kg]
weight lighting : 64.0 [kg]
weight 210 bar hydraulic system : 123.8 [kg]
weight engine-driven 40kVA electricity generators : 48.5 [kg]
weight ram air turbine for emergency electric power : 5.0 [kg]
weight 22Ah battery : 28.5 [kg]
weight controls : 19.4 [kg]
weight systems : 619.9 [kg]
total weight fuselage : 24149 [kg](21.3 [%])
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total weight aluminium ribs (44 ribs) : 3756 [kg]
weight engine mounts : 170 [kg]
weight 2 wing fuel tanks empty for total 16428 [litre] fuel : 246 [kg]
weight 171 [litre] vent surge tanks : 20 [kg]
weight wing covering (painted aluminium 4.72 [mm]) : 4723 [kg]
total weight aluminium spars (multi-cellular wing structure) : 4903 [kg]
weight wings : 13382 [kg]
weight wing/square meter : 72.24 [kg]
weight bleed air thermal leading-edge anti-icing : 41.9 [kg]
weight ailerons (4.5 [m2]) : 128.9 [kg]
weight fin (34.4 [m2]) : 1246.4 [kg]
weight rudder (11.6 [m2]) : 404.2 [kg]
weight tailplane (horizontal stabilizer) (50.4 [m2]): 2005.1 [kg]
weight elevators (12.5 [m2]): 244.1 [kg]
weight paint wing & tail surfaces : 113.4 [kg]
/image7.png)
Delta airlines 757-200 landing with double slotted flaps and leading edge slats deployed
weight flight control hydraulic servo actuators: 40.7 [kg]
weight trailing-edge double slotted flaps (30.4 [m2]) : 937.8 [kg]
weight leading edge slats (18.4 [m2]) : 368.1 [kg]
weight aluminium honeycomb spoilers (12.8 [m2]) : 213.0 [kg]
total weight wing construction : 19562 [kg] (33.0 [%])
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tire pressure main wheels : 11.95 [Bar] (nitrogen), ply rating : 22 PR
tire speed limit : 338 [km/hr]
total tyre footprint : 0.35 [m2]
Runway LCN at MTOW (0.76m radius of rigidity) : 83 [ ]
Aircraft Classification Number (ACN), MTOW on rigid runway and medium subgrade strength (B) : 43 [ ]
Can only operate from unpaved runways with reduced weight and reduced tyre pressure
wheel pressure : 12473.8 [kg]
wheel track : 7.32 [m] wheelbase : 18.29 [m]
weight 8 Dunlop 40.2 x 14.6 main wheels (1020 [mm] by 370 [mm]) : 812.1 [kg]
weight 2 nose wheels : 101.5 [kg]
weight multi-disc wheel-brakes : 98.2 [kg]
weight Hydro-air flywheel detector type anti-skid units : 9.0 [kg]
weight oleo-pneumatic shock absorbers : 111.3 [kg]
weight wheel hydraulic operated retraction system : 1240.3 [kg]
weight undercarriage struts (four-wheel bogies) with axle 3767.2 [kg]
total weight landing gear : 6139.6 [kg] (5.4 [%]
*******************************************************************
/image8.png)
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calculated empty weight : 57773 [kg](50.9 [%])
weight oil for 9.6 hours flying : 6.9 [kg]
unusable fuel in engine and tanks 170.7 litre fuel : 134.0 [kg]
weight lifejackets : 87.3 [kg]
weight 3 life rafts : 121.2 [kg]
weight catering : 210.1 [kg]
weight water : 290.0 [kg]
weight crew : 648 [kg]
weight crew luggage, navigation chards, flight docs (NOTOC), manuals, miscellaneous items : 93 [kg]
operational weight empty : 59364 [kg] (52.4 [%])
********************************************************************
weight 194 passengers : 14938 [kg]
weight luggage : 3104 [kg]
weight cargo : 6055 [kg] (cargo + luggage/m3 belly : 150 [kg/m3])
zero fuel weight (ZFW): 83461 [kg](73.6 [%])
weight fuel for landing (1.7 hours flying) : 6350 [kg]
max. landing weight (MLW): 89811 [kg](79.2 [%])
max. fuel weight : 92871 [kg] (81.9 [%])
payload with max fuel : 221 passengers + luggage 20527 [kg]
can be operated with high density seating with max.fuel for good economics
published maximum take-off weight : 113398 [kg] (100.0 [%])
Boe/image9.png)
calculation : * 4 * (engine power)
power loading (Take-off) : 334 [kg/KN]
power loading (Take-off) 1 PUF: 667 [kg/KN]
max. total take-off power : 340.0 [KN]
calculation : *5* (loads)
manoeuvre load : 1.0 [g] at 9000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.4 [g]
design flight time : 2.65 [hours]
design cycles : 25500 sorties, design hours : 67575 [hours]
max. wing loading (MTOW & flaps retracted) : 612 [kg/m2]
wing stress (2 g) during operation : 149 [N/kg] at 2g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.88 ["]
max. angle of attack (stalling angle, clean) : 12.21 ["]
max. angle of attack (full flaps) : 19.91 ["]
angle of attack at economic cruise speed : 3.50 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.16 [ ]
lift coefficient at max. speed : 0.27 [ ]
lift coefficient at max. angle of attack (clean): 1.20 [ ]
max. lift coefficient 50 [° ] flap setting : 2.23 [ ]
drag coefficient at max. speed : 0.0341 [ ]
drag coefficient at econ. cruise speed : 0.0358 [ ]
induced drag coefficient at econ. cruise speed : 0.0122 [ ]
drag coefficient (zero lift) : 0.0236 [ ]
lift/drag ratio at econ. speed : 7.98 [ ]
calculation : *8* (speeds
minimum unstick speed (Vmu) at TO angle 13.2 ° : 288 [km/u] (156 [kt])
take-off decision speed (V1) : 263 [km/u] (142 [kt])
/image10.png)
Dutchbird flew with 3 Boeing 757-200 ’s (PH-DBA, PH-DBB en PH-DBH, leased from Condor ). Seen here is a Dutchbird taking of at Schiphol airport. They have PW2037 engines.
/image11.png)
take-off rotation speed (VR) : 291 [km/u] (157 [kt])
lift-off speed (VLOF) : 317 [km/u] (171 [kt]) at pitch angle : 10.6 [°]
take-off safety speed (V2) : 320 [km/u] (173 [kt])
flap retraction speed (V3) at 500m (OW loaded : 109616 [kg]): 343 [km/u] (185 [kt])
steady initial climb speed (V4) : 346 [km/u] (187 [kt])
climb speed (to FL150 with 63 [%] power) : 613 [km/hr] (331 [kt])
max. endurance speed (Vbe): 605 [km/u] min. fuel/hr : 3585 [kg/hr] at height : 7315 [m]
max. range speed (Vbr): 819 [km/u] (0.78 [mach]) min. fuel consumption : 4.39 [kg/km] at cruise height : 11582 [m]
max. cruising speed : 885 [km/hr] (478 [kt]) at 10000 [m] (power:25 [%])
max. operational speed (Mmo) : 960 [km/hr] (Mach 0.86 ) at 7500 [m] (power:36 [%])
airflow at cruise speed per engine : 367.0 [kg/s]
speed of thrust jet : 1306 [km/hr]
initial descent speed 10000 - 7315 [m]: Mach 0.75
descent speed 7315 - 3048 [m]: 537 [km/u] (290 [kt])
approach speed 3048 - 500 [m] (clean): 463 [km/u] (250 [kt])
minimum control speed (MCS) Vmca (clean): 356 [km/u] (192 [kt])
stalling speed clean at 500 [m] height at Max.Landing Weight : 89811 [kg]): 297 [km/u] (160 [kt])
final approach speed (landing speed) at sea-level with 50 [°] flaps VREF (max. landing weight): 245 [km/u] (132 [kt])
ICAO Aircraft Approach Category (APC) : C
stalling speed at sea-level with full flaps VSO (max. landing weight): 188 [km/u] (102 [kt]
rate of climb (max. continous power) at sea-level ROC (loaded, 63 % power) : 1227 [m/min]
rate of climb at sea-level ROC (loaded, 75 % power) : 1654 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 63 % power on remaining engines) : 120 [m/min]
rate of descent from FL240 to FL100 (7315m > 3048m): 914 [m/min] (2999 [ft/min])
rate of descent during approach with landing gear extended, with use of spoilers: 457 [m/min] (8 [m/s])
calculation : *9* (regarding various performances)
ICAO Aerodrome Reference Code : 4D
Brake kinetic energy capacity : 1740 [KW]
/image12.png)
FAR takeoff runway length at MTOW 113398 kg (250000 lb), standard day, sea level, dry runway : 8600 ft > 2621m
FAR TO runway length (TOFL) requirement at TOW 113398 [kg] standard day at SL (PUF after V1): 2620 [m]
Take-off flap setting : 10 [° ]
+++ FAA certification landing distance : +++
landing weight : 89811 [kg], TE flap setting : 50 [°]
runway condition : dry , landing over 50ft (15m) at threshold at sea-level
with use of thrust reversers, glideslope : 3.5 [°]
/image13.png)
Landing RW length over 15m, dry RW, sea level at MLW 89800 [kg] (197970lb) : 4800 ft = 1463 [m]
FAA approved landing field length at SL, dry runway : 1445 [m] (4742 [ft])
FAA approved landing field length at SL, wet runway: 1649 [m] (5409 [ft])
max. lift/drag ratio : 13.48 [ ]
climb to 5000 [m] with max payload : 3.77 [min]
climb to 10000 [m] with max payload : 11.60 [min]
descent time from 10000 [m] to 250 [m] : 24.33 [min]
max. ceiling fully loaded (mtow- 60 min.fuel): 109616 [kg] ) : 15200 [m]
ceiling limited by max. pressure differential 16225 [m]
max. theoretical ceiling (OWE + 60 min.fuel) : 18100 [m] with flying weight :63146 [kg]
calculation *10* (action radius & endurance)
range with max. payload: 6551 [km] with 24097.0 [kg] max. useful load (89.3 [%] fuel)*
range with high density pax: 7006 [km] with 239 passengers (94.9 [%] fuel)*
range with typical two-class pax: 7556 [km] with 194 passengers (100.0 [%] fuel)*
/image14.png)
Range with max payload (MZFW 83461 kg > 184000lb) : 3200nm > 5925 km
Range with max fuel (MTOW 113398 kg) : 3810 nm > 7055 km
Ferry range (OEW 59364 kg) : 4650 nm > 8610 km
range with max.fuel and MTOW : 7425 [km] with 8 crew and 221 passengers and 0 [kg] cargo*
ferry range (calculated): 8582 [km] with 2 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 70089 [litre] fuel : 13133 [km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 1641171 [paskm]
useful load with range 1000km : 24097 [kg]
useful load with range 1000km : 239 passengers
production (theor.max load): 21326 [tonkm/hour]
production (useful load): 21326 [tonkm/hour]
production (passengers): 196223 [paskm/hour]
oil and fuel consumption per tonkm : 0.177 [kg]
calculation *11* (operating cost)
fuel cost per hour at econ.speed (4817 [litre]):2890 [eur] (39 [pax-km/litre fuel])
fuel cost per seat 1000km flight (222 [pax] 2-class seating): 15.56 [eur/1000PK]
oil cost per hour: 3 [eur]
/image15.png)
Delta airlines stewardess adjusting the seats
crew cost per hour : 1050 [eur]
list price 2024 : 133 [mln USD]
average flying hours in 1 year : 3350 [hours] technical life : 20 [year]
real average service life : 20 [years]
depreciation : 20 [years] to 10% residual value
financing interest per flying hour : 893 [EUR]
write off per flying hour : 1649 [EUR]
mean time between engine failure (MTBF) : 18210 [hr]
insufficient engine reability for ETOPS flights
can continue fly on 1 engine, low risk for emergency landing for PUF
/image16.png)
workhours per day : 11.78 [hr]
average flight hours till crash : 8.38 [mln hr] (2500 service years)
safe flight hours till fatality : 146930 [hr] (43.9 service years)
reservation pax liability/flying hour : 0.88 [SDR*] (1.10 [eur])
insurance cost per hour : 73 [eur] insurance rate : 0.5 [%]
engine maintenance cost per hour : 1556.4 [eur]
wing maintenance cost per hour : 153.8 [eur]
fuselage maintenance cost per hour : 119.66 [eur]
tire life (time till worn out) : 98 [cycles]
maintenance cost per hour (excluding engines): 1003 [eur]
direct operating cost per hour: 9118 [eur], DOC per km : 10.88 [eur]
DOC per seat 1000km flight (222 [pax] 2-class seating): 46.47 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 43.11 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 0.43 [eur/kg] (= DOC/tonkm)
passenger service charge (depart at Schiphol): 11.34 [eur]
security service charge (depart at Schiphol): 10.08 [eur]
airport take-off fee / passenger : 3.35 [eur/pax]
airport landing fee / passenger : 3.35 [eur/pax]
retour ticket price 1000km trip : 164.08 [eur/pax]
price retour ticket Schiphol-Barcelona : 189.64 [eur/pax]*
/image17.png)
accidents with fatalities > see the accident file
Literature :
https://contentzone.eurocontrol.int/aircraftperformance/default.aspx ?
Jane’s all the world aircraft ‘90-’91 page 380
Air international oct’98 page 252
Aircraft – Boeing 757-200 – Northwest Airlines History Center
https://contentzone.eurocontrol.int/aircraftperformance/default.aspx?
https://www.boeing.com/commercial/airports/plan-manuals
rescue : https://www.boeing.com/commercial/airports/rescue-fire
confidence rating regarding source data : medium - all information is only available from news, social media or unofficial sources
DISCLAIMER Above calculations are based on published data, they must be
regarded as indication not as facts.
Calculated performance and weight may not correspond with actual weights
and performances and are assumptions for which no responsibility can be taken.
Calculations are as accurate as possible, they can be fine-tuned when more data
is available, you are welcome to give suggestions and additional information
so we can improve our program. For copyright on drawings/photographs/
content please mail to below mail address
(c) B van der Zalm 14 April 2025 contact : info.aircraftinvestigation@gmail.com ac jetpax 2020.py python 3.7.4
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