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weight and performance calculations for the Boeing 737-900
***** PRELIMINARY FILE ****
Boeing 737-9K2 PH-BXO c/n 29599 “Plover” parked at the gate at Schiphol
Boeing 737-900
role : jet airliner
importance : ****
first flight : 3 August 2000 operational : May 2001 (Alaska Airlines)
country : United States of America
design :
production : 55 aircraft (total 737 production 5500 aircraft)
general information :
Longest 737. The 737-900 is 2.63m longer than the -800. On 10 September 1997 it was decided to put the -900 into production. It is a competitor of the A321. The -900 may carry a maximum of 189 passengers. This number is limited by the number of doors and emergency exits. This makes the -900 unpopular with low-cost carriers that cannot carry the maximum number of passengers due to the available space and the maximum paying load. That is why Boeing developed the 737-900ER that has extra doors and can now carry as many as 215 passengers. Sales of the -900 are slow. At the beginning of 1999, KLM ordered 4 -900s for USD 230 million.
Boeing 737-900 prototype N737X
By May 1998, a total of 4,000,7 37s had been sold to 280 users in 100 countries. At any time of the day, there are 825,737s in the air. Every 6 seconds a 737 starts somewhere !
2022 there have been no fatal accidents with a 737-900.
primary users : Korean Air (11), KLM (4), Alaska Airlines (10), Continental (15)
Accommodation:
flight crew : 2 cabin crew : 6
passengers : seating for 176 in two class : 12 business class and 164 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 : 34.31 [m], length : 42.11 [m], height : 12.55 [m]
wing area : 125.0 [m^2] fuselage exterior width : 3.76 [m]
weights :
operating empty weight : 42901 [kg] max. structural payload : 20738 [kg]
Zero Fuel weight (ZFW) : 63639 [kg] max. landing weight (MLW) : 66361 [kg]
max.take-off weight : 78840 [kg] weight fuel : 20828 [kg] (26035 [liter])
performance :
Max. operating Mach number (Mmo) : 0.88 [Mach] (974 [km/hr]) at 7620 [m]
normal cruise speed : 938 [km/hr] (Mach 0.89 ) at 11582 [m] (33 [%] power)
economic cruise speed : 844 [km/hr] (Mach 0.80 ) at 11582 [m]
service ceiling : 12500 [m]
range with max fuel : 4975 [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 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
N75410
calculation : *1* (dimensions)
measured wing chord : 6.39 [m] at root
mean wing chord : 3.64 [m]
calculated average wing chord tapered wing with rounded tips: 3.65 [m]
wing aspect ratio : 9.42 []
seize (span*length*height) : 18132 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 6.4 [kg/hr]
fuel consumption (econ. cruise speed) : 3288.8 [kg/hr] (4111.0 [litre/hr]) at 28 [%] power
distance flown for 1 kg fuel : 0.26 [km/kg] at 11582 [m] height, sfc : 55.4 [kg/KN/h]
total fuel capacity : 26035 [litre] (20828 [kg])
calculation : *3* (weight)
weight engine(s) dry : 4740.0 [kg] = 22.20 [kg/KN]
weight 59 litre oil tank : 4.99 [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 61.4 [kg]
weight engine cowling 555.1 [kg]
weight thrust reversers 85.4 [kg]
total weight propulsion system : 5459 [kg](6.9 [%])
***************************************************************
Accommodation cabin facilities:
typical 2-class cabin layout for 176 passengers : economy : pitch : 81.3 [cm] ( 3+3 ) seating in 29.7 rows
weight seats : 920.0 [kg]
high density seating passengers : 189 [pax] at 6 -abreast seating in 31.5 rows, pitch 78.7 [cm] (31-in)
pax density, normal seating : 0.60 [m2/pax], high density seating : 0.56 [m2/pax]
weight 4 lavatories : 55.5 [kg]
weight 3 galleys : 207.3 [kg]
weight overhead stowage for hand luggage : 61.6 [kg]
weight 4 wardrobe closets : 35.2 [kg]
Delta 737-900 interior
weight 61 windows : 55.3 [kg]
weight 4 1.83x0.86 [m] entrance/exit doors : 194.2 [kg]
weight 2 freight doors (belly) : 77.1 [kg]
belly baggage/cargo hold volume front : 21.98 [m3]
belly baggage/cargo hold volume rear : 28.55 [m3]
passenger compartment volume : 136 [m3]
passenger cabin max.width : 3.53 [m] cabin length : 31.08 [m] cabin height : 2.20 [m]
floor area : 106.0 [m2]
weight cabin facilities : 1606.2 [kg]
safety facilities:
weight 4 over wing emergency exits : 92.5 [kg]
weight 9 hand fire extinguisher : 26 [kg]
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators : 114.4 [kg]
weight emergency flare installation : 10 [kg]
weight 4 emergency evacuation slides : 150.4 [kg]
weight safety equipment & facilities : 413 [kg]
fuselage construction:
fuselage aluminium frame : 11408 [kg]
floor loading (payload/m2): 196 [kg/m2]
weight rear pressure bulkhead : 153.1 [kg]
fuselage covering ( 369.9 [m2] duraluminium 2.63 [mm]) : 2555.3 [kg]
weight floor beams : 598.7 [kg]
weight cabin furbishing : 927.4 [kg]
weight cabin floor : 1477.3 [kg]
fuselage (sound proof) isolation : 267.1 [kg]
weight 8703 [litre] main central fuel tanks empty : 487.4 [kg]
weight empty waste tank : 18 [kg]
weight fuselage structure : 17891.4 [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 : 358 [m3]
weight air-conditioning and pressurisation system : 215 [kg]
weight APU / engine starter: 53.4 [kg]
weight lighting : 58.1 [kg]
weight engine-driven 40kVA electricity generators : 44.0 [kg]
weight controls : 17.6 [kg]
weight systems : 387.8 [kg]
total weight fuselage : 20379 [kg](25.8 [%])
***************************************************************
total weight aluminium ribs (1105 ribs) : 2811 [kg]
weight engine mounts : 107 [kg]
weight 6 fuel tanks empty for total 17332 [litre] fuel : 971 [kg]
weight wing covering (painted aluminium 4.04 [mm]) : 2724 [kg]
total weight aluminium spars (multi-cellular wing structure) : 2344 [kg]
weight wings : 7880 [kg]
weight wing/square meter : 63.04 [kg]
weight thermal leading-edge anti-icing : 37.7 [kg]
weight fin & rudder (13.7 [m2]) : 863.4 [kg]
weight stabilizer & elevator (14.1 [m2]): 887.5 [kg]
weight flight control hydraulic servo actuators: 57.6 [kg]
Alaska airlines 737-900 N323AS landing with double slotted flaps extended
weight double slotted flaps (21.1 [m2]) : 571.1 [kg]
weight leading edge slats (6.8 [m2]) : 121.0 [kg]
weight spoilers (4.6 [m2]) : 26.2 [kg]
total weight wing surfaces & bracing : 11522 [kg] (14.6 [%])
*******************************************************************
tyre pressure main wheels : 14.40 [Bar] (nitrogen), ply rating : 28 PR
Can only operate from paved runways
wheel pressure : 17344.8 [kg]
weight 4 Dunlop main wheels (1130 [mm] by 420 [mm]) : 990.3 [kg]
weight 2 nose wheels : 247.6 [kg]
weight multi-disc wheel-brakes : 63.6 [kg]
weight flywheel detector type anti-skid units : 5.4 [kg]
weight oleo-pneumatic shock absorbers : 84.9 [kg]
weight wheel hydraulic operated retraction system : 803.6 [kg]
weight undercarriage struts with axle 1782.5 [kg]
total weight landing gear : 3977.8 [kg] (5.0 [%]
*******************************************************************
********************************************************************
calculated empty weight : 41338 [kg](52.4 [%])
weight oil for 6.4 hours flying : 48.7 [kg]
weight lifejackets : 79.2 [kg]
weight 3 life rafts : 110.0 [kg]
weight catering : 345.5 [kg]
weight water : 276.4 [kg]
weight crew : 648 [kg]
weight crew lugage,nav.chards,flight doc.,miscell.items : 56 [kg]
operational weight empty : 42901 [kg] (54.4 [%])
********************************************************************
weight 176 passengers : 13552 [kg]
weight luggage : 2816 [kg]
weight cargo : 4370 [kg] (cargo+luggage/m3 belly : 128 [kg/m3])
zero fuel weight (ZFW): 63639 [kg](80.7 [%])
weight fuel for landing (0.8 hours flying) : 2722 [kg]
max. landing weight (MLW): 66361 [kg](84.2 [%])
max. fuel weight : 63729 [kg] (80.8 [%])
payload with max fuel : 162 passengers+luggage 15111 [kg]
published maximum take-off weight : 78840 [kg] (100.0 [%])
Korean Air 737-9B5 HL7707
calculation : * 4 * (engine power)
power loading (Take-off) : 369 [kg/KN]
power loading (Take-off) 1 PUF: 739 [kg/KN]
max. total take-off power : 213.5 [KN]
calculation : *5* (loads)
manoeuvre load : 5.1 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 1.2 [g]
design flight time : 3.93 [hours]
design cycles : 24005 sorties, design hours : 94252 [hours]
max. wing loading (MTOW & flaps retracted) : 631 [kg/m2]
wing stress (2 g) during operation : 180 [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) : 11.07 ["]
max. angle of attack (full flaps) : 10.27 ["]
angle of attack at max. speed : 1.50 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.28 [ ]
lift coefficient at max. angle of attack : 1.13 [ ]
max. lift coefficient full flaps : 1.63 [ ]
drag coefficient at max. speed : 0.0397 [ ]
drag coefficient at econ. cruise speed : 0.0512 [ ]
induced drag coefficient at econ. cruise speed : 0.0151 [ ]
drag coefficient (zero lift) : 0.0361 [ ]
lift/drag ratio at max. speed : 7.14 [ ]
calculation : *8* (speeds
stalling speed clean at sea-level (OW loaded : 75551 [kg]): 333 [km/u]
stalling speed at sea-level with full flaps (normal landing weight): 234 [km/u]
landing speed at sea-level (normal landing weight : 66050 [kg]): 270 [km/hr]
approach speed at sea-level with full flaps (normal landing weight): 305 [km/u]
max. rate of climb speed : 551 [km/hr] at sea-level
max. endurance speed : 449 [km/u] min. fuel/hr : 2999 [kg/hr] at height : 4572 [m]
max. range speed : 893 [km/u] min. fuel consumption : 3.877 [kg/km] at cruise height : 11582 [m]
cruising speed : 938 [km/hr] at 11582 [m] (power:31 [%])
max. operational speed (Mmo) : 974.00 [km/hr] (Mach 0.88 ) at 7620 [m] (power:46.2 [%])
airflow at cruise speed per engine : 166.0 [kg/s]
speed of thrust jet : 1652 [km/hr]
climbing speed at sea-level (loaded) : 1341 [m/min]
climbing speed at 1000 [m] with 1 engine out (PUF / MTOW) : 353 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 356.3 [km/u]
high wheel pressure, can only take off from paved runways
Runway length (79000 KG TOW, sea level, standard day 15°C) 2800M
take-off distance at sea-level concrete runway : 2756 [m]
take-off distance at sea-level over 15 [m] height : 2859 [m]
landing run : 1403 [m]
Landing field length (dry runway at sea-level, Max. landing weight) : 1800 [m]
landing run (C.A.R.) from 15 [m] at SL, dry runway : 1806 [m]
landing run (C.A.R.) from 15 [m] at SL, wet runway : 2106 [m]
737-9K2 PH-BXP skidded off the runway on 12 August 2006 with 190 passengers when leaving the Polderbaan Runway at Schiphol. There are no injuries.
lift/drag ratio : 12.40 [ ]
climb to 5000 [m] with max payload : 3.53 [min]
climb to 10000 [m] with max payload : 5.93 [min]
theoretical ceiling fully loaded (mtow- 60 min. fuel:75551 [kg] ) : 14900 [m]
calculation *10* (action radius & endurance)
range with max. payload: 3807 [km] with 20738.0 [kg] max. useful load (73.0 [%] fuel)
range with high density pax: 4662 [km] with 189 passengers (88.2 [%] fuel)
range with typical two-class pax: 4995 [km] with 176 passengers (94.0 [%] fuel)
range with max.fuel : 5345 [km] with 8 crew and 162 passengers and 100.0 [%] fuel
ferry range : 6096 [km] with 2 crew and zero payload (100.0 [%] fuel)
Ferry range 3500 NM = 6475 km, max fuel range 2700 nm = 4995 km
max range theoretically with additional fuel tanks total 46308.7 [litre] fuel : 10176 [km]
Available Seat Kilometres (ASK) : 879165 [paskm]
useful load with range 1000km : 20738 [kg]
useful load with range 1000km : 189 passengers
production (theor.max load): 19452 [tonkm/hour]
production (useful load): 19452 [tonkm/hour]
production (passengers): 165088 [paskm/hour]
oil and fuel consumption per tonkm : 0.169 [kg]
fuel cost per paskm : 0.020 [eur]
crew cost per paskm : 0.006 [eur]
economic hours : 55750 [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 : 0.004 [eur]
insurance per paskm : 0.0006 [eur]
maintenance cost per paskm : 0.014 [eur]
direct operating cost per paskm : 0.045 [eur]
direct operating cost per tonkm (max. load): 0.383 [eur]
direct operating cost per tonkm (normal useful load): 0.383 [eur]
Literature :
wikipedia
https://contentzone.eurocontrol.int/aircraftperformance/default.aspx?
https://www.boeing.com/search/results.html?q=airplane+characteristics
www.boeing.com
vliegtuighomepage.nl
Air International maart’99 page 136
Air International okt’98 page 207
Luchtvaart mrt’99 page 8
Flight International 31 jan’00 page 16a
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