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weight and performance calculations for the Boeing 757-200 (PW2037)

***** PRELIMINARY FILE ****

Delta Airlines Boeing 757-231 N723TW c/n 29378 taking off from Los Angeles Int’l apt.(LAX) , October 2013

Boeing 757-200 (PW2037)

role : jet airliner

importance : ****

first flight : 14 March 1984 operational : November 1984

country : United States of America

design :

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 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. ^[2]

primary users : Delta airlines, Northwest airlines, Aeroperu

Accommodation:

flight crew : 2 cabin crew : 6

passengers : seating for 186 in two class : 16 business class and 170 economy deluxe class seats ( 33 -in pitch)

exit limit : 239 passengers

engine : 2 Pratt & Whitney PW2037 turbofan engines of 170.0 [KN] (38216.9 [lbf])

dimensions :

wingspan : 38.05 [m], length : 47.32 [m], height : 13.56 [m]

wing area : 185.25 [m^2] fuselage exterior width : 3.76 [m]

weights :

empty weight : 57039 [kg]

operating empty weight : 59350 [kg] max. structural payload : 24100 [kg]

Zero Fuel weight (ZFW) : 83450 [kg] max. landing weight (MLW) : 89800 [kg]

max.take-off weight : 104350 [kg] weight fuel : 34144 [kg] (42680 [liter])

performance :

Max. operating Mach number (Mmo) : 0.86 [Mach] (960 [km/hr]) at 7500 [m]

normal cruise speed : 885 [km/hr] (Mach 0.82 ) at 10000 [m] (27 [%] power)

economic cruise speed : 863 [km/hr] (Mach 0.80 ) at 10000 [m]

service ceiling : 11674 [m]

range with max fuel : 7408 [km] (ATA domestic fuel reserves - 370.0 [km] alternate)

description :

low-wing cantilever monoplane with retractable landing gear with nose wheel

two spar fail-safe wing structure

with double slotted flaps with slotted LE flaps (slats) ,with spoilers airfoil : NACA with supercritical cross-section

sweep angle 3/4 chord: 25.0 [°]

engines and landing gear attached to the wings, fuel tanks in the wings and fuselage

construction : all-metal aluminium-alloy stressed-skin construction with pressurized fuselage

fuselage shape : 0

calculation : *1* (dimensions)

measured wing chord : 4.87 [m] at 50% wingspan

mean wing chord : 4.87 [m]

calculated average wing chord tapered wing with rounded tips: 4.81 [m]

wing aspect ratio : 7.82 []

seize (span*length*height) : 24415 [m^3]

calculation : *2* (fuel consumption)

oil consumption : 34.0 [kg/hr]

fuel consumption (econ. cruise speed) : 3788.4 [kg/hr] (4735.5 [litre/hr]) at 31 [%] power

distance flown for 1 kg fuel : 0.23 [km/kg] at 10000 [m] height, sfc : 35.5 [kg/KN/h]

total fuel capacity : 42680 [litre] (34144 [kg])

calculation : *3* (weight)

weight engine(s) dry : 6442.0 [kg] = 18.95 [kg/KN]

weight 417 litre oil tank : 35.42 [kg]

oil tank filled with 2.1 litre oil : 1.9 [kg]

oil in engine 4.2 litre oil : 3.7 [kg]

fuel in engine 18.6 litre fuel : 13.60 [kg]

weight fuel lines 78.8 [kg]

weight engine cowling 884.0 [kg]

weight thrust reversers 136.0 [kg]

total weight propulsion system : 7595 [kg](7.3 [%])

***************************************************************

Accommodation cabin facilities:

typical 2-class cabin layout for 186 passengers : economy : pitch : 83.8 [cm] ( 3+3 ) seating in 31.5 rows

weight seats : 970.0 [kg]

high density seating passengers : 239 [pax] at 6 -abreast seating in 39.8 rows, pitch 73.7 [cm]

pax density, normal seating : 0.62 [m2/pax], high density seating : 0.48 [m2/pax]

weight 4 lavatories : 66.0 [kg]

weight 3 galleys : 191.1 [kg]

weight overhead stowage for hand luggage : 65.1 [kg]

weight 4 wardrobe closets : 37.2 [kg]

weight 65 windows : 58.6 [kg]

weight 8 1.83x0.86 [m] entrance/exit doors : 517.5 [kg]

weight 2 freight doors (belly) : 102.7 [kg]

cabin volume (usable), excluding flight deck : 315.72 [m3]

passenger cabin max.width : 3.52 [m] cabin length : 36.29 [m] cabin height : 2.06 [m]

floor area : 115.1 [m2]

weight cabin facilities : 2008.2 [kg]

safety facilities:

weight 9 hand fire extinguisher : 27 [kg]

weight lifejackets : 83.7 [kg]

weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]

weight oxygen masks & oxygen generators : 120.9 [kg]

weight emergency flare installation : 10 [kg]

weight 8 emergency evacuation slides : 87.4 [kg]

weight safety equipment & facilities : 349 [kg]

Delta airlines stewardess adjusting the seats

fuselage construction:

fuselage aluminium frame : 17351 [kg]

floor loading (payload/m2): 209 [kg/m2]

weight rear pressure bulkhead : 201.5 [kg]

fuselage covering ( 422.2 [m2] duraluminium 3.48 [mm]) : 3866.8 [kg]

weight floor beams : 806.1 [kg]

weight cabin furbishing : 945.7 [kg]

weight cabin floor : 1656.1 [kg]

fuselage (sound proof) isolation : 305.5 [kg]

weight 7130 [litre] main central fuel tanks empty : 399.3 [kg]

weight fuselage structure : 25531.6 [kg]

Avionics:

weight HF and UHF radio : 7.0 [kg]

weight dual cloud-collision radar : 25.0 [kg]

weight VOR/ILS,RMI,Doppler,radio altimeter : 12.0 [kg]

weight Integrated Flight System / auto-pilot : 23.0 [kg]

weight artificial horizons, compass, alti-meters : 7 [kg]

weight engine monitoring gauches & control switches : 6 [kg]

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

weight avionics : 80.0 [kg]

Systems:

Air-conditioning and pressurisation system maintains sea level conditions up to 6550 [m]

and gives equivalent of 2000 [m] at 11200 [m]. pressure differential : 0.59 [bars] (kg/cm2)

weight air-conditioning and pressurisation system : 261 [kg]

weight APU / engine starter: 85.0 [kg]

weight lighting : 61.4 [kg]

weight engine-driven 40kVA electricity generators : 46.5 [kg]

weight controls : 19.4 [kg]

weight systems : 473.8 [kg]

total weight fuselage : 28443 [kg](27.3 [%])

***************************************************************

total weight aluminium ribs (1095 ribs) : 3721 [kg]

weight engine mounts : 170 [kg]

weight 6 fuel tanks empty for total 35550 [litre] fuel : 1991 [kg]

weight wing covering (painted aluminium 3.65 [mm]) : 3649 [kg]

total weight aluminium spars (multi-cellular wing structure) : 3406 [kg]

weight wings : 10776 [kg]

weight wing/square meter : 58.17 [kg]

weight thermal leading-edge anti-icing : 41.9 [kg]

weight fin & rudder (16.8 [m2]) : 980.1 [kg]

weight stabilizer & elevator (20.8 [m2]): 1213.7 [kg]

weight flight control hydraulic servo actuators: 65.3 [kg]

weight double slotted flaps (31.3 [m2]) : 779.1 [kg]

weight leading edge slats (10.1 [m2]) : 164.3 [kg]

weight spoilers (6.8 [m2]) : 35.0 [kg]

757-200 N557NW rolling out at RW26 Phoenix airport, November 2005, with extended thrust reversers, deployed spoilers and flaps.

total weight wing surfaces & bracing : 16217 [kg] (15.5 [%])

*******************************************************************

tyre pressure main wheels : 11.81 [Bar] (nitrogen), ply rating : 22 PR

Can only operate from paved runways

wheel pressure : 11478.5 [kg]

weight 8 Dunlop main wheels (1020 [mm] by 355 [mm]) : 742.5 [kg]

weight 2 nose wheels : 92.8 [kg]

weight mult-disc wheel-brakes : 83.5 [kg]

weight flywheel detector type anti-skid units : 9.0 [kg]

weight oleo-pneumatic shock absorbers : 111.3 [kg]

weight wheel hydraulic operated retraction system : 1094.1 [kg]

weight undercarriage struts (four-wheel bogies) with axle 3282.7 [kg]

total weight landing gear : 5415.9 [kg] (5.2 [%]

*******************************************************************

********************************************************************

calculated empty weight : 57671 [kg](55.3 [%])

weight oil for 10.0 hours flying : 367.7 [kg]

weight catering : 318.5 [kg]

weight water : 254.8 [kg]

weight crew : 648 [kg]

weight crew lugage,nav.chards,flight doc.,miscell.items : 90 [kg]

operational weight empty : 59350 [kg] (56.9 [%])

********************************************************************

weight 186 passengers : 14322 [kg]

weight luggage : 2976 [kg]

weight cargo : 6802 [kg]

zero fuel weight (ZFW): 83450 [kg](80.0 [%])

weight fuel for landing (1.7 hours flying) : 6350 [kg]

max. landing weight (MLW): 89800 [kg](86.1 [%])

max. fuel weight : 93494 [kg] (89.6 [%])

payload with max fuel : 117 passengers+luggage 10856 [kg]

published maximum take-off weight : 104350 [kg] (100.0 [%])

calculation : * 4 * (engine power)

power loading (Take-off) : 307 [kg/KN]

power loading (Take-off) 1 PUF: 614 [kg/KN]

max. total take-off power : 340.0 [KN]

On October 2, 1996, the 757-23A N52AW of Aeroperu 73km NW of Lima plunges into the sea. All 61 passengers and 9 crew members are killed. Flight 603 from Lima (LIM) to Santiago (SCL). 5 minutes after take-off, the crew reports that there are problems with the instruments and that they are returning to the airport. Due to conflicting values on the instruments, they lose control and plunge into the sea. Location +-5km 11°43'55"S 77°42'20"W

cause blocked pitot tube, pitot tube on the left wing was covered with piece of adhesive tape during maintenance, forgot to remove. c/n 25489/505 ^1st flight 1992 2630 cycles PW2037 engines

calculation : *5* (loads)

manoeuvre load : 5.6 [g] at 1000 [m]

limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 1.2 [g]

design flight time : 3.42 [hours]

design cycles : 21729 sorties, design hours : 74420 [hours]

max. wing loading (MTOW & flaps retracted) : 563 [kg/m2]

wing stress (2 g) during operation : 176 [N/kg] at 2g emergency manoeuvre

calculation : *6* (angles of attack)

angle of attack zero lift : -1.76 ["]

max. angle of attack (stalling angle, clean) : 11.68 ["]

max. angle of attack (full flaps) : 10.88 ["]

angle of attack at max. speed : 1.28 ["]

calculation : *7* (lift & drag ratios

lift coefficient at angle of attack 0° : 0.15 [ ]

lift coefficient at max. speed : 0.26 [ ]

lift coefficient at max. angle of attack : 1.15 [ ]

max. lift coefficient full flaps : 1.65 [ ]

drag coefficient at max. speed : 0.0440 [ ]

drag coefficient at econ. cruise speed : 0.0486 [ ]

induced drag coefficient at econ. cruise speed : 0.0081 [ ]

drag coefficient (zero lift) : 0.0404 [ ]

lift/drag ratio at max. speed : 5.90 [ ]

Boeing 757-222 N591UA photographed on September 8, 2001

On September 11, 2001 ("Nine-Eleven") United Airlines' 757-222 N591UA is hijacked by 4 hijackers with the aim of crashing into a government building (probably the White House).

130km SE v Pittsburgh,hijacked, Flight UA93 New York-Newark(EWR) to San Francisco(SFO), Crashed in a forest in Stoney Creek, Somerset Country (PA), south of Indian Lake apt, near Buckstown. Passengers have tried to overpower the hijackers. Probably that is why the plane crashed in a forest and not on the White House. The FBI's conclusion was that hijackers flew the plane into the ground because they were afraid that the passengers would take control of the aircraft. All 38 passengers and 7 crew members were killed. 2006 there is a film about this fatal flight : United 93, first flight 1996 c/n 28142/718 18435 flight hours 6968 cycles PW2037 engines. Location : +-100m 40°03'11.43"N 78°54'07.54"W

calculation : *8* (speeds

stalling speed clean at sea-level (OW loaded : 100562 [kg]): 313 [km/u]

stalling speed at sea-level with full flaps (normal landing weight): 223 [km/u]

landing speed at sea-level (normal landing weight : 89513 [kg]): 256 [km/hr]

max. rate of climb speed : 539 [km/hr] at sea-level

max. endurance speed : 549 [km/u] min. fuel/hr : 2831 [kg/hr] at height : 9144 [m]

max. range speed : 809 [km/u] min. fuel consumption : 4.041 [kg/km] at cruise height : 10973 [m]

cruising speed : 885 [km/hr] at 10000 [m] (power:32 [%])

max. operational speed (Mmo) : 960.00 [km/hr] (Mach 0.86 ) at 7500 [m] (power:46.7 [%])

airflow at cruise speed per engine : 367.0 [kg/s]

speed of thrust jet : 1426 [km/hr]

climbing speed at sea-level (loaded) : 1577 [m/min]

climbing speed at 1000 [m] with 1 engine out (PUF / MTOW) : 441 [m/min]

calculation : *9* (regarding various performances)

take-off speed : 337.8 [km/u]

high wheel pressure, can only take off from paved runways

take-off distance at sea-level concrete runway : 1945 [m]

take-off distance at sea-level over 15 [m] height : 2031 [m]

landing run : 1313 [m]

landing run (C.A.R.) from 15 [m] : 1976 [m]

lift/drag ratio : 10.74 [ ]

climb to 5000 [m] with max payload : 2.96 [min]

climb to 10000 [m] with max payload : 4.97 [min]

theoretical ceiling fully loaded (mtow- 60 min. fuel:100562 [kg] ) : 15400 [m]

calculation *10* (action radius & endurance)

range with max. payload: 4638 [km] with 24100.0 [kg] max. useful load (61.2 [%] fuel)

range with high density pax: 5079 [km] with 239 passengers (66.8 [%] fuel)

range with typical two-class pax: 6232 [km] with 186 passengers (81.1 [%] fuel)

range with max.fuel : 7778 [km] with 8 crew and 117 passengers and 100.0 [%] fuel

ferry range : 8125 [km] with 2 crew and zero payload (100.0 [%] fuel)

max range theoretically with additional fuel tanks total 57574.1 [litre] fuel : 10730 [km]

Available Seat Kilometres (ASK) : 1159133 [paskm]

useful load with range 1000km : 24100 [kg]

useful load with range 1000km : 239 passengers

production (theor.max load): 21328 [tonkm/hour]

production (useful load): 21328 [tonkm/hour]

production (passengers): 164610 [paskm/hour]

oil and fuel consumption per tonkm : 0.179 [kg]

fuel cost per paskm : 0.023 [eur]

crew cost per paskm : 0.006 [eur]

economic hours : 22300 [hours] is less then design hours

time between engine failure : 962 [hr]

can continue fly on 1 engine, low risk for emergency landing for PUF

writing off per paskm : 0.013 [eur]

insurance per paskm : 0.0009 [eur]

maintenance cost per paskm : 0.022 [eur]

direct operating cost per paskm : 0.066 [eur]

direct operating cost per tonkm (max. load): 0.507 [eur]

direct operating cost per tonkm (normal useful load): 0.507 [eur]

Delta airlines 757-200 landing with double slotted flaps and leading edge slats deployed

Literature :

Boeing 757 - Wikipedia

https://contentzone.eurocontrol.int/aircraftperformance/default.aspx?

https://www.boeing.com/search/results.html?q=airplane+characteristics

Jane’s all the world aircraft ‘90-’91 page 380

Air international oct’98 page 252

Aircraft – Boeing 757-200 – Northwest Airlines History Center

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 22 October 2022 contact : info.aircraftinvestigation@gmail.com python 3.7.4