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weight and performance calculations for the Boeing 737-800
***** PRELIMINARY FILE ****
KLM 737-8K2 PH-BXE c/n 29595 at the gate at Schiphol airport ©bvdz
Boeing 737-800
role : jet airliner
importance : ****
first flight : 31 July 1997 operational : April 1998 (Hapag Lloyd)
country : United States of America
design :
production : May 2019 : 4979 737-800’s at Renton
general information :
September 1994 final decision to build the 737-800. At that time, 4 airlines had ordered 40 aircraft. The -800 is based on the -400 but has been extended by 2.79m. It was initially referred to as -400X. It is the heaviest 737 and can carry 160 passengers over 5380km. In November 1995, Transavia ordered 8 aircraft with options for 12 more, worth 460 million NLG.
The 737-800 burns 850 US gallons (3,200 L) of jet fuel per hour—about 80 percent of the fuel used by an MD-80 on a comparable flight, while carrying more passengers. The Airline Monitor, an industry publication, quotes a 737-800 fuel burn of 4.88 US gal (18.5 L) per seat per hour, compared to 5.13 US gal (19.4 L) for the A320. In 2011, United Airlines — flying a Boeing 737-800 from Houston to Chicago—operated the first U.S. commercial flight powered by a blend of algae-derived biofuel and traditional jet fuel to reduce its carbon footprint .
In early 2017, a new 737-800 was valued at $48.3 million, falling to below $47 million by mid-2018. By 2025, a 17-year-old 737-800W will be worth $9.5 million and leased for $140,000 per month. The 737-800 is the best selling 737NG variant and is the most widely used narrow-body aircraft.
primary users : Hapag-Lloyd, Transavia, Ryanair, Kenia Airlines, GOL, Turkish Airlines, Ethiopian airlines, Air India express
Accommodation:
flight crew : 2 cabin crew : 5
passengers : seating for 160 in two class : 12 business class and 148 economy class seats ( 32 -in pitch)
exit limit : 189 passengers
engine : 2 GE-Snecma CFM56-7B24 turbofan engines of 106.75 [KN] (23998.0 [lbf])
dimensions :
wingspan : 34.32 [m], length : 39.47 [m], height : 12.55 [m]
wing area : 124.6 [m^2] fuselage exterior width : 3.76 [m]
weights :
operating empty weight : 41404 [kg] max. structural payload : 20276 [kg]
Zero Fuel weight (ZFW) : 61680 [kg] max. landing weight (MLW) : 65310 [kg]
max.take-off weight : 78245 [kg] weight fuel : 20824 [kg] (26030 [liter])
performance :
Max. operating Mach number (Mmo) : 0.82 [Mach] (920 [km/hr]) at 7160 [m]
normal cruise speed : 880 [km/hr] (Mach 0.81 ) at 9150 [m] (32 [%] power)
economic cruise speed : 829 [km/hr] (Mach 0.76 ) at 9150 [m]
service ceiling : 12500 [m]
range with max fuel : 5436 [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 and spoilers, with slotted LE flaps (slats) airfoil : NACA with supercritical cross-section
sweep angle 3/4 chord: 25.0 [°]
Ryanair , the Irish low-cost airline , is among the largest operators of the Boeing 737-800, with a fleet of over 400 of the -800 variant serving routes across Europe, Middle East, and North Africa.
engines attached with pylons to the wing, main 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 : 6.39 [m] at root
mean wing chord : 3.63 [m]
calculated average wing chord tapered wing with rounded tips: 3.63 [m]
wing aspect ratio : 9.45 []
seize (span*length*height) : 17000 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 6.4 [kg/hr]
fuel consumption (econ. cruise speed) : 2973.3 [kg/hr] (3716.7 [litre/hr]) at 25 [%] power
distance flown for 1 kg fuel : 0.28 [km/kg] at 9150 [m] height, sfc : 55.4 [kg/KN/h]
total fuel capacity : 26030 [litre] (20824 [kg])
calculation : *3* (weight)
weight engine(s) dry : 4740.0 [kg] = 22.20 [kg/KN]
weight 64 litre oil tank : 5.48 [kg]
oil tank filled with 1.3 litre oil : 1.2 [kg]
oil in engine 2.6 litre oil : 2.3 [kg]
fuel in engine 11.7 litre fuel : 8.54 [kg]
weight fuel lines 54.3 [kg]
weight engine cowling 555.1 [kg]
weight thrust reversers 85.4 [kg]
total weight propulsion system : 5452 [kg](7.0 [%])
***************************************************************
Accommodation cabin facilities:
typical 2-class cabin layout for 160 passengers : economy : pitch : 81.3 [cm] ( 3+3 ) seating in 27.1 rows
Aeroflot layout : 22 rows x 6 = 132 pax + 4 = 136 econ. seats + 5 rows x 4 abreast = 20 business class seats, total 156 seats
weight seats : 835.0 [kg]
high density seating passengers : 187 [pax] at 6 -abreast seating in 31.2 rows, pitch 73.7 [cm]
pax density, normal seating : 0.60 [m2/pax], high density seating : 0.52 [m2/pax]
weight 4 lavatories : 53.5 [kg]
weight 2 galleys : 127.7 [kg]
weight overhead stowage for hand luggage : 56.0 [kg]
weight 3 wardrobe closets : 32.0 [kg]
weight 56 windows : 50.5 [kg]
weight 4 1.83x0.86 [m] entrance/exit doors : 197.5 [kg]
weight 2 freight doors (belly) : 78.4 [kg]
belly baggage/cargo hold volume front : 19.63 [m3]
belly baggage/cargo hold volume rear : 25.50 [m3]
passenger compartment volume : 125 [m3]
passenger cabin max.width : 3.53 [m] cabin length : 28.44 [m] cabin height : 2.20 [m]
floor area : 96.7 [m2]
weight cabin facilities : 1430.7 [kg]
safety facilities:
weight 4 over wing emergency exits : 94.1 [kg]
weight 8 hand fire extinguisher : 24 [kg]
weight lifejackets : 72.0 [kg]
The 737-800 has slide-rafts and normal rafts for overwater flights
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators : 104.0 [kg]
weight emergency flare installation : 10 [kg]
weight 4 emergency evacuation slides : 136.7 [kg]
weight safety equipment & facilities : 461 [kg]
fuselage construction:
fuselage aluminium frame : 10773 [kg]
floor loading (payload/m2): 210 [kg/m2]
weight rear pressure bulkhead : 155.7 [kg]
fuselage covering ( 343.3 [m2] duraluminium 2.67 [mm]) : 2412.8 [kg]
weight floor beams : 594.6 [kg]
weight cabin furbishing : 846.1 [kg]
weight cabin floor : 1347.4 [kg]
fuselage (sound proof) isolation : 248.1 [kg]
weight 8703 [litre] main central fuel tanks empty : 487.4 [kg]
weight empty waste tank : 16 [kg]
weight fuselage structure : 16881.1 [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 gauges & control switches : 6 [kg]
weight avionics : 80.0 [kg]
Systems:
Air-conditioning and pressurisation system maintains sea level conditions up to 6275 [m]
and gives equivalent of 2000 [m] at 10700 [m]. pressure differential : 0.57 [bars] (kg/cm2)
pressurized fuselage volume : 328 [m3]
weight air-conditioning and pressurisation system : 196 [kg]
weight APU / engine starter: 53.4 [kg]
weight lighting : 52.8 [kg]
weight engine-driven 40kVA electricity generators : 40.0 [kg]
weight controls : 16.9 [kg]
weight systems : 359.1 [kg]
total weight fuselage : 19212 [kg](24.6 [%])
***************************************************************
total weight aluminium ribs (1101 ribs) : 2790 [kg]
weight engine mounts : 107 [kg]
weight 6 fuel tanks empty for total 17327 [litre] fuel : 970 [kg]
weight wing covering (painted aluminium 4.08 [mm]) : 2745 [kg]
total weight aluminium spars (multi-cellular wing structure) : 2353 [kg]
weight wings : 7888 [kg]
weight wing/square meter : 63.30 [kg]
weight thermal leading-edge anti-icing : 37.8 [kg]
weight fin & rudder (13.7 [m2]) : 867.5 [kg]
weight stabilizer & elevator (14.0 [m2]): 888.3 [kg]
weight flight control hydraulic servo actuators: 57.8 [kg]
weight double slotted flaps (21.1 [m2]) : 571.6 [kg]
weight leading edge slats (6.8 [m2]) : 121.1 [kg]
weight spoilers (4.6 [m2]) : 26.3 [kg]
total weight wing surfaces & bracing : 11509 [kg] (14.7 [%])
*******************************************************************
tyre pressure main wheels : 14.40 [Bar] (nitrogen), ply rating : 28 PR
Can only operate from paved runways
wheel pressure : 17213.9 [kg]
weight 4 Dunlop main wheels (1130 [mm] by 420 [mm]) : 981.0 [kg]
weight 2 nose wheels : 245.2 [kg]
weight multi-disc wheel-brakes : 61.7 [kg]
weight flywheel detector type anti-skid units : 5.4 [kg]
weight oleo-pneumatic shock absorbers : 82.2 [kg]
weight wheel hydraulic operated retraction system : 843.6 [kg]
weight undercarriage struts with axle 1956.7 [kg]
total weight landing gear : 4175.9 [kg] (5.3 [%]
*******************************************************************
Transavia 737-8K2 PH-HZA c/n 28373 June 2001 at Schiphol
********************************************************************
calculated empty weight : 40349 [kg](51.6 [%])
weight oil for 7.4 hours flying : 53.8 [kg]
weight catering : 212.9 [kg]
weight water : 170.3 [kg]
weight crew : 567 [kg]
weight crew lugage,nav.chards,flight doc.,miscell.items : 51 [kg]
operational weight empty : 41404 [kg] (52.9 [%])
********************************************************************
weight 160 passengers : 12320 [kg]
weight luggage : 2560 [kg]
weight cargo : 5396 [kg] (cargo+luggage/m3 belly : 162 [kg/m3])
zero fuel weight (ZFW): 61680 [kg](78.8 [%])
weight fuel for landing (1.2 hours flying) : 3630 [kg]
max. landing weight (MLW): 65310 [kg](83.5 [%])
max. fuel weight : 62228 [kg] (79.5 [%])
payload with max fuel : 172 passengers+luggage 16017 [kg]
published maximum take-off weight : 78245 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 366 [kg/KN]
power loading (Take-off) 1 PUF: 733 [kg/KN]
max. total take-off power : 213.5 [KN]
calculation : *5* (loads)
manoeuvre load : 4.6 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 1.2 [g]
The KLM & Transavia 787-8K2 did not have winglets
design flight time : 2.66 [hours]
design cycles : 29028 sorties, design hours : 77254 [hours]
max. wing loading (MTOW & flaps retracted) : 628 [kg/m2]
wing stress (2 g) during operation : 178 [N/kg] at 2g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.69 ["]
max. angle of attack (stalling angle, clean) : 11.06 ["]
max. angle of attack (full flaps) : 10.26 ["]
angle of attack at max. speed : 1.67 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.30 [ ]
lift coefficient at max. angle of attack : 1.13 [ ]
max. lift coefficient full flaps : 1.63 [ ]
drag coefficient at max. speed : 0.0308 [ ]
drag coefficient at econ. cruise speed : 0.0355 [ ]
induced drag coefficient at econ. cruise speed : 0.0087 [ ]
drag coefficient (zero lift) : 0.0268 [ ]
lift/drag ratio at max. speed : 9.70 [ ]
calculation : *8* (speeds
stalling speed clean at sea-level (OW loaded : 75272 [kg]): 333 [km/u]
stalling speed at sea-level with full flaps (normal landing weight): 233 [km/u]
landing speed at sea-level (normal landing weight : 65118 [kg]): 268 [km/hr]
approach speed at sea-level with full flaps (normal landing weight): 303 [km/u]
max. rate of climb speed : 635 [km/hr] at sea-level
max. endurance speed : 467 [km/u] min. fuel/hr : 2556 [kg/hr] at height : 3962 [m]
max. range speed : 919 [km/u] min. fuel consumption : 3.088 [kg/km] at cruise height : 11582 [m]
KLM 737-8K2 PH-BXC in the foreground being refuelled and serviced, with PH-BXN c/n 30356 “Blackbird” and PH-BXI in the background at a busy Schiphol airport
cruising speed : 880 [km/hr] at 9150 [m] (power:27 [%])
max. operational speed (Mmo) : 920.00 [km/hr] (Mach 0.82 ) at 7160 [m] (power:33.5 [%])
airflow at cruise speed per engine : 211.2 [kg/s]
speed of thrust jet : 1369 [km/hr]
climbing speed at sea-level (loaded) : 1631 [m/min]
climbing speed at 1000 [m] with 1 engine out (PUF / MTOW) : 497 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 355.6 [km/u]
high wheel pressure, can only take off from paved runways
take-off distance at sea-level concrete runway : 2247 [m]
take-off distance at sea-level over 15 [m] height : 2345 [m]
landing run : 1578 [m]
landing run (C.A.R.) from 15 [m] at SL, dry runway : 2373 [m]
landing run (C.A.R.) from 15 [m] at SL, wet runway : 2673 [m]
lift/drag ratio : 14.42 [ ]
climb to 5000 [m] with max payload : 2.90 [min]
climb to 10000 [m] with max payload : 4.87 [min]
theoretical ceiling fully loaded (mtow- 60 min. fuel:75272 [kg] ) : 14200 [m]
calculation *10* (action radius & endurance)
possible additional cargo : 1137 [kg]
range with max. payload: 4548 [km] with 20276.0 [kg] max. useful load (79.5 [%] fuel)
range with high density pax: 5394 [km] with 187 passengers (93.4 [%] fuel)
range with typical two-class pax: 5854 [km] with 160 passengers (100.0 [%] fuel)
range with max.fuel : 5806 [km] with 7 crew and 172 passengers and 100.0 [%] fuel
ferry range : 6496 [km] with 2 crew and zero payload (100.0 [%] fuel)
max range theoretically with additional fuel tanks total 47036.5 [litre] fuel : 11124 [km]
Available Seat Kilometres (ASK) : 936577 [paskm]
useful load with range 1000km : 20276 [kg]
Hapag-Lloyd 737-8K5 D-AHFU c/n 30414
useful load with range 1000km : 187 passengers
production (theor.max load): 17843 [tonkm/hour]
production (useful load): 17843 [tonkm/hour]
production (passengers): 140800 [paskm/hour]
oil and fuel consumption per tonkm : 0.167 [kg]
fuel cost per paskm : 0.021 [eur]
crew cost per paskm : 0.006 [eur]
economic hours : 22300 [hours] is less then design hours
time between engine failure : 865 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
writing off per paskm : 0.011 [eur]
insurance per paskm : 0.0011 [eur]
maintenance cost per paskm : 0.015 [eur]
direct operating cost per paskm : 0.054 [eur]
direct operating cost per tonkm (max. load): 0.425 [eur]
direct operating cost per tonkm (normal useful load): 0.425 [eur]
Literature :
Boeing 737 Next Generation - Wikipedia
https://contentzone.eurocontrol.int/aircraftperformance/default.aspx?
https://www.boeing.com/search/results.html?q=airplane+characteristics
Air International aug’85 blz.95
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
KLM 737-800 PH-BXE being refuelled at Schiphol airport, summer 2001
(c) B van der Zalm 22 October 2022 contact : info.aircraftinvestigation@gmail.com python 3.7.4