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weight and performance calculations for the Boeing 787-9

KLM Boeing 787-9 PH-BHN c/n 42491 taking off from Schiphol, 29 November 2024, with destination Osaka. © bvdz

Boeing 787-9

role : wide-body long-range airliner

importance : ****

first flight : 17 September 2013 (Paine Field) operational : August 2014 (Air New

Zealand)

country : United States of America

ICAO aircraft type designator : B789

production : 639 aircraft

general information :

Lengthened and strengthened version with a 6.1m longer fuselage and higher MTOW.

Designed as replacement for the Boeing 767-300ER and Airbus A330-300. It competes

with the A330-900. The wing, fuselage and systems were revised to achieve the needed

performance.

primary users : Air New Zealand, United Airlines, ANA, KLM, Air China

Accommodation:

flight crew : 2 cabin crew : 9

passengers : seating for 290 in two class : 28 business class and 262 economy class

seats ( 32 -in pitch) exit limit : 420 passengers, high density seating for 404

passengers

engine : 2 General Electric GEnx-1B70/P2 turbofan engines of 321.6 [KN] (72297 [lbf])

Tailangle measured : 8°

dimensions :

wingspan : 60.12 [m], length overall: 62.81 [m], length of fuselage : 62.00 [m]

height : 17.02 [m] wing area gross : 377.0 [m^2] fuselage exterior width : 5.77 [m]

weights :

operating empty weight : 129000 [kg] max. structural payload : 52436 [kg]

Zero Fuel weight (ZFW) : 181436 [kg] max. landing weight (MLW) : 192776 [kg]

max. take-off weight : 254700 [kg] weight usable fuel : 99247 [kg] (126429 [litres])

performance :

Max. operating Mach number (Mmo) : 0.89 [Mach] (956 [km/hr]) at 10000 [m]

critical Mach speed : 0.85 [Mach]

max. cruising speed : 903 [km/hr] (Mach 0.85 ) at 11000 [m] (36 [%] power)

economic cruising speed : 880 [km/hr] (Mach 0.83 ) at 11000 [m]

service ceiling : 13100 [m]

range with max fuel and MTOW : 15186 [km] (ATA domestic fuel reserves - 370.0 [km]

alternate)

description :

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

engines attached with pylons to the wing, main landing gear attached to the wings, fuel

tanks in the wings and fuselage

Wings : tapered multi-cellular fail safe wing with carbon-fiber-reinforced polymer

composite material wing surfaces with trailing edge single-slotted Fowler flaps with

full-span slotted LE flaps (slats) ,with spoilers (outboard) and airbrakes (inboard)

and with raked wingtips. Airfoil : Boeing airfoil with supercritical cross-section

average thickness/chord ratio : 12.7 [%], sweep angle 3/4 chord: 32.2 [°]

incidence : 2.00 [°], dihedral : 8.0 [°]

Fuselage : Pressurized CFRP semi-monocoque fail safe structure of circular section

calculation : *1* (dimensions)

measured wing chord at root: 11.93 [m]

measured wing chord at tip : 1.75 [m]

taper ratio : 0.147 [ ]

mean wing chord : 6.27 [m]

wing aspect ratio : 9.59 []

Oswald factor (e): 0.701 []

seize (span*length*height) : 64270 [m^3]

calculation : *2* (fuel consumption)

oil consumption : 1.9 [kg/hr]

fuel consumption (econ. cruise speed) : 5614.4 [kg/hr] (7152.1 [litre/hr]) at 19 [%] power

distance flown for 1 kg fuel : 0.16 [km/kg] at 11000 [m] height, sfc : 47.0 [kg/KN/h]

total fuel capacity : 126429 [litre] (99247 [kg])

calculation : *3* (weight)

weight engine(s) dry : 12294.0 [kg] = 19.11 [kg/KN]

weight 59.1 litre oil tank : 5.02 [kg]

oil tank filled with 4.1 litre oil : 3.6 [kg]

oil in engine 7.9 litre oil : 7.1 [kg]

weight all fuel lines and pumps containing 126 litres fuel : 174.4 [kg]

weight engine cowling : 1672.3 [kg]

Scoot Boeing 787-9 9V-OJF c/n 37119 at Guangzhou airport (CAN), China, August 2021

weight thrust reversers : 964.8 [kg]

total weight propulsion system : 15121 [kg](5.9 [%])

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

Accommodation cabin facilities:

typical 2-class cabin layout for 290 passengers : economy : pitch : 81.3 [cm] 32.0 [-in]

( 3+3+3 ) seating in 33.8 rows

business class pitch : 215.9 [cm] 85.0 [-in] at 6 -abreast

weight passenger seats : 1836.9 [kg]

weight cabin crew seats : 45.0 [kg]

weight flight crew seats : 42.0 [kg]

weight 2 jump seats in the cockpit :14.0 [kg]

high density seating passengers : 404 [pax] at mainly 9 -abreast seating in 46.4 rows,

pitch 76.2 [cm] 30.0 [-in]

pax density, normal seating : 0.87 [m2/pax], high density seating : 0.63 [m2/pax]

passenger cabin luxurious spaced for good service, enough space for galleys and toilets

even at HD seating

weight 9 lavatories : 362.8 [kg]

weight overhead flight crew and cabin crew rest compartment : 268.0 [kg]

weight 6 galleys : 939.6 [kg]

weight overhead stowage for hand luggage (total : 33.1 [m3]) : 113.1 [kg]

weight 3 wardrobe closets : 29.0 [kg]

KLM 787-9 interior

weight 290 entertainment LCD screens in back of seats : 145.0 [kg]

weight 70 windows (47 x 27 cm) made of electrochromism-based smart glass : 210.1

[kg]

weight 8 (1.93 x 1.07 [m]) Type A main entry doors : 511.1 [kg]

weight 3 (main door size : 1.70 x 2.69 [m]) freight doors (belly) : 559.8 [kg]*

total usable belly baggage/cargo hold volume : 209.6 [m3]

underfloor belly hold can accommodate : 36 LD3 containers, netto volume : 161.1 [m3]

and : 11.4 [m3] usable bulk cargo

cabin volume (usable), excluding flight deck : 725 [m3]

passenger compartment volume : 416 [m3]

passenger cabin max width : 5.50 [m] cabin length : 46.73 [m] max cabin height : 2.87

[m] floor area : 253.5 [m2]

weight cabin facilities : 5076.3 [kg]

safety facilities:

evacuation time with 404 passengers : 49 [sec]

weight 8 hand fire extinguisher : 25 [kg]

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

weight oxygen masks & oxygen generators (deploy cabin alt.>4267m): 188.5 [kg]

weight emergency flare installation : 10 [kg]

weight 8 emergency evacuation slides : 380.3 [kg]

weight safety equipment & facilities : 624 [kg]

fuselage construction:

fuselage CFRP frame : 23032 [kg]

floor loading (payload/m2): 207 [kg/m2]

weight rear pressure bulkhead : 349.3 [kg]

fuselage covering ( 856.1 [m2] CFRP 3.94 [mm]) : 5346.3 [kg]

weight paint fuselage : 179.8 [kg]

weight aluminium-lithium alloy floor beams : 4559.0 [kg]

weight cabin furbishing : 4331.1 [kg]

weight cabin floor : 3526.4 [kg]

weight (sound proof) isolation : 531.4 [kg] TO-noise level : 89.8 [EPNdB]

weight 84258 [litre] main central fuel tanks empty : 1685.2 [kg]

weight empty 1089 [litre] potable water tanks : 96.4 [kg]

weight empty waste tank : 54.1 [kg]

weight fuselage structure : 43690.8 [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 IIIB auto-landing system : 10.0 [kg]

weight multi-function LCD screens with Cockpit Display System Interfaces to User Systems / ARINC 661 : 16 [kg]

The 787 has a Head-up display

weight head-up display (HUD) : 10 [kg]

weight Ethernet (Avionics Full-Duplex Switched Ethernet (AFDX) / ARINC 664) : 8 [kg]

weight ground proximity warning system (GPWS) : 6 [kg]

weight reserve ADI, ASI, alti-meter, compass, engine temp. and rpm indicators : 15 .

[kg]

weight avionics : 158.0 [kg]

Systems:

Electrically powered (bleedless) air-conditioning and pressurization system maintains

sea level conditions up to 7300 [m] and gives equivalent of 1800 [m] at 11885 [m].

pressure differential : 0.63 [bar] (kg/cm2) pressurized fuselage volume : 1079 [m3]

cabin air refreshment time : 3.6 [min]

weight air-conditioning and pressurization system : 509 [kg]

weight APU / engine starter : 160.8 [kg]

weight lighting (LED): 95.7 [kg]

weight triple redundant 207 bar hydraulic system with electrically-driven pumps

(bleedless system): 277.1 [kg]

weight two engine-driven 90kVA 400Hz 3-phase AC electricity generators delivering

1.45 MW : 72.5 [kg]

weight ram air turbine for emergency electric power : 5.0 [kg]

weight three 24V 25Ah Li-ion batteries : 85.5 [kg]

weight controls (yoke Fly-By-Wire): 18.3 [kg]

weight systems : 1218.9 [kg]

total weight fuselage : 50768 [kg](19.9 [%])

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

total weight aluminium-lithium alloy ribs (1936 ribs) : 8477 [kg]

weight titanium engine pylons : 322 [kg]

weight 2 wing fuel tanks empty for total 42171 [litre] fuel : 633 [kg]

weight 506 [litre] vent surge tanks : 61 [kg]

weight wing covering CFRP 4.45 [mm]) : 5370 [kg]

load on front upper spar (clmax) per running metre : 21108.7 [N]

load on rear upper spar (vmax) per running metre : 12880.0 [N]

total weight CFRP spars (multi-cellular wing structure) : 20954 [kg]

Air Europa 787-9 EC-MTI c/n 62169 taking off from Schiphol airport, March 2024 © bvdz

weight wings : 34801 [kg]

weight wing/square meter : 92.31 [kg]

weight electro-thermal leading-edge anti-icing : 66.1 [kg]

weight high & low speed ailerons (10.2 [m2]) : 378.6 [kg]

weight fin (81.3 [m2]) : 3756.7 [kg]

weight rudder (24.4 [m2]) : 1082.8 [kg]

weight tailplane (stabilizer) (52.1 [m2]): 2648.4 [kg]

weight elevators (22.3 [m2]): 557.8 [kg]

weight paint wing & tail surfaces : 214.3 [kg]

weight flight control hydraulic servo actuators: 107.1 [kg]

weight trailing-edge single slotted Fowler flaps (56.55 [m2]) : 1700.4 [kg]

weight track-mounted light alloy construction leading edge slats (42.23 [m2]) : 1043.1

[kg]

weight spoilers made of CFRP with Spoiler Electro-Mechanical Actuators (SEMA) (14.7

[m2]) : 296.1 [kg]

weight airbrakes (18.2 [m2]) : 411.4 [kg]

total weight wing construction : 48079 [kg] (37.3 [%])

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

tire pressure main wheels : 15.80 [Bar] (nitrogen), ply rating : 38 PR

tire speed limit : 376 [km/hr]

total tyre footprint : 1.17 [m2]

Runway LCN at MTOW (0.76m radius of rigidity) : 64 [ ]

Aircraft Classification Number (ACN), MTOW on flexible runway and medium

subgrade strength (B) : 72 [ ]

Can only operate from paved runways subgrade A

wheel pressure : 28017.0 [kg]

wheel track : 9.80 [m] wheelbase : 25.83 [m]

weight 8 Dunlop 54 x 21 main wheels (1370 [mm] by 533 [mm]) : 2425.8 [kg]

weight 2 nose wheels : 303.2 [kg]

weight carbon wheel-brakes : 181.4 [kg]

weight Duplex anti-skid units : 9.0 [kg]

weight oleo-pneumatic shock absorbers : 241.9 [kg]

weight wheel hydraulic operated retraction system : 2332.7 [kg]

weight titanium undercarriage struts (four-wheel bogies) with axle 6052.7 [kg]

total weight landing gear : 11546.8 [kg] (4.5 [%]

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

Air New Zealand, launch customer of the Boeing 787-9, ZK-NZE c/n 34334

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

calculated empty weight : 125515 [kg](49.3 [%])

weight oil for 20.2 hours flying : 40.9 [kg]

unusable fuel in engine and tanks 505.7 litre fuel : 397.0 [kg]

weight lifejackets : 130.5 [kg]

weight 5 life rafts : 181.2 [kg]

weight catering : 698.6 [kg]

weight water : 964.0 [kg]

weight crew : 891 [kg]

weight crew luggage, navigation chards, flight docs (NOTOC), manuals, miscellaneous

items : 182 [kg]

operational weight empty : 129000 [kg] (50.6 [%])

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

weight 290 passengers : 22330 [kg]

weight luggage : 4640 [kg]

weight cargo : 25466 [kg] (cargo + luggage/m3 belly : 138 [kg/m3])

zero fuel weight (ZFW): 181436 [kg](71.2 [%])

weight fuel for landing (2.0 hours flying) : 11340 [kg]

max. landing weight (MLW): 192776 [kg](75.7 [%])

max. fuel weight : 228247 [kg] (89.6 [%])

payload with max fuel : 284 passengers + luggage 26453 [kg]

published maximum take-off weight : 254700 [kg] (100.0 [%])

United Boeing 787-9 N27958 c/n 36406, Melbourne, April 2024

calculation : * 4 * (engine power)

power loading (Take-off) : 396 [kg/KN]

power loading (Take-off) 1 PUF: 792 [kg/KN]

max. total take-off power : 643.2 [KN]

calculation : *5* (loads)

manoeuvre load : 0.8 [g] at 9000 [m]

limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.2 [g]

design flight time : 6.00 [hours]

design cycles : 13470 sorties, design hours : 80820 [hours]

max. wing loading (MTOW & flaps retracted) : 676 [kg/m2]

wing stress (2 g) during operation : 126 [N/kg] at 2g emergency manoeuvre

calculation : *6* (angles of attack)

angle of attack zero lift : -1.79 ["]

max. angle of attack (stalling angle, clean) : 10.60 ["]

max. angle of attack (full flaps) : 14.80 ["]

angle of attack at economic cruise speed : 3.71 ["]

calculation : *7* (lift & drag ratios

lift coefficient at angle of attack 0° : 0.16 [ ]

lift coefficient at max. speed : 0.40 [ ]

lift coefficient at max. angle of attack (clean): 1.10 [ ]

max. lift coefficient full flaps : 2.12 [ ]

drag coefficient at max. speed : 0.0282 [ ]

drag coefficient at econ. cruise speed : 0.0291 [ ]

induced drag coefficient at econ. cruise speed : 0.0114 [ ]

drag coefficient (zero lift) : 0.0177 [ ]

lift/drag ratio at econ. speed : 14.17 [ ]

calculation : *8* (speeds

take-off decision speed (V1) : 304 [km/u] (164 [kt])

take-off rotation speed (VR) : 308 [km/u] (166 [kt])

minimum unstick speed (Vmu) at TO angle 11.0 ° : 301 [km/u] (162 [kt])

lift-off speed (VLOF) : 331 [km/u] (179 [kt]) at pitch angle : 9.1 [°]

KLM 787-9 PH-BHG c/n 38766 taking-off from Schiphol, Aalsmeerbaan 29 November 2024 with destination Dubai

take-off safety speed (V2) : 334 [km/u] (180 [kt])

flap retraction speed (V3) at 500m (OW loaded : 249086 [kg]): 374 [km/u] (202 [kt])

steady initial climb speed (V4) : 359 [km/u] (194 [kt])

climb speed (to FL150 with 92 [%] power) : 803 [km/hr] (434 [kt])

max. endurance speed (Vbe): 665 [km/u] min. fuel/hr : 5480 [kg/hr] at height : 8230 [m]

max. range speed (Vbr): 885 [km/u] (0.84 [mach]) min. fuel consumption : 6.27 [kg/km] at cruise height : 11582 [m]

max. cruising speed : 903 [km/hr] (488 [kt]) at 11000 [m] (power:19 [%])

max. operational speed (Mmo) : 956 [km/hr] (Mach 0.89 ) at 10000 [m] (power:23 [%])

airflow at cruise speed per engine : 570.1 [kg/s]

speed of thrust jet : 1294 [km/hr]

initial descent speed 10000 - 7315 [m]: Mach 0.72

descent speed 7315 - 3048 [m]: 537 [km/u] (290 [kt])

approach speed 3048 - 500 [m] (clean): 426 [km/u] (230 [kt])

minimum control speed (MCS) Vmca (clean): 381 [km/u] (206 [kt])

stalling speed clean at 500 [m] height at Max.Landing Weight : 192776 [kg]): 317

[km/u] (171 [kt])

final approach speed (landing speed) at sea-level with full flaps VREF (max. landing weight): 265 [km/u] (143 [kt])

ICAO Aircraft Approach Category (APC) : D

stalling speed at sea-level with full flaps VSO (max. landing weight): 204 [km/u] (110

[kt]

rate of climb at sea-level ROC (loaded, 92 % power) : 2244 [m/min]

rate of climb at sea-level ROC (loaded, 75 % power) : 1608 [m/min]

rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 92 % power on remaining engines) : 506 [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)

high wheel pressure, can only take off from paved runways

ICAO Aerodrome Reference Code : 4E

Brake kinetic energy capacity : 4324 [KW]

Take-off runway length at MTOW 254700kg, standard day, sea level : 9950ft > 3035m

FAR TO runway length (TOFL) requirement at TOW 254700 [kg] standard day at SL:

(distance to 10.7m height x 1.15): 3119 [m]

+++ FAA certification landing distance : +++

landing weight : 192776 [kg], TE flap setting : 30 [°]

runway condition : dry , landing over 50ft (15m) at threshold at sea-level

without use of thrust reversers

Landing runway length with MLW 192776 kg at sea level, dry runway, flaps 30° : 5900 ft > 1800m

FAA approved landing field length at SL, dry runway : 1802 [m] (5912 [ft])

landing distance (C.A.R.) from 15 [m] at SL, wet runway: 2069 [m] (6786 [ft])

max. lift/drag ratio : 17.25 [ ]

climb to 5000 [m] with max payload : 2.06 [min]

climb to 10000 [m] with max payload : 6.34 [min]

descent time from 10000 [m] to 250 [m] : 24.33 [min]

max. ceiling fully loaded (mtow- 60 min.fuel): 249086 [kg] ) : 14400 [m]

ceiling limited by max. pressure differential 16825 [m]

max. theoretical ceiling (OWE + 60 min.fuel) : 17700 [m] with flying weight : 134614

[kg]

calculation *10* (action radius & endurance)

range with max. payload: 10925 [km] with 52436.0 [kg] max. useful load (73.8 [%]

fuel)*

range with high density pax: 13530 [km] with 404 passengers (88.8 [%] fuel)*

range with typical two-class pax: 15460 [km] with 290 passengers (99.5 [%] fuel)*

Range with max. payload : 5300nm > 9815 km

Range with max fuel : 8200nm > 15185 km

Ferry range with zero payload : 9300nm > 17225 km

range with max.fuel : 15556 [km] with 11 crew and 284 passengers and 100.0 [%]

fuel*

ferry range (calculated): 17328 [km] with 2 crew and zero payload (100.0 [%] fuel)*

max range theoretically with additional fuel tanks total 163174 [litre] fuel : 21202

[km]*

* calculated ranges without fuel reserves

Available Seat Kilometres (ASK) : 5265595 [paskm]

useful load with range 1000km : 52436 [kg]

useful load with range 1000km : 404 passengers

production (theor.max load): 47350 [tonkm/hour]

production (useful load): 47350 [tonkm/hour]

production (passengers): 331741 [paskm/hour]

oil and fuel consumption per tonkm : 0.119 [kg]

calculation *11* (operating cost)

fuel cost per hour (7152 [litre]):4291 [eur] (46 [pax-km/litre fuel])

fuel cost per seat 1000km flight (367 [pax] 2-class seating): 12.93 [eur/1000PK]

oil cost per hour: 8 [eur]

crew cost per hour : 1500 [eur]

list price 2024 : 290 [mln USD]

average flying hours in 1 year : 4000 [hours] technical life : 20 [year]

real average service life : 22 [years]

depreciation : 24 [years] to 10% residual value

economic hours (expected total flying hours) : 96000 [hours]

financing interest per flying hour : 1630 [EUR]

write off per flying hour : 2735 [EUR]

time between engine failure : 14965 [hr]

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

workhours per day : 12.33 [hr]

no fatalities during service life > 100%% safe

average flight hours till crash : 22.80 [mln hr] (5700 service years)

safe flight hours till fatality : 22799520 [hr] (5699.9 service years)

reservation pax liability/flying hour : 0.01 [SDR*] (0.01 [eur])

insurance cost per hour : 59 [eur] insurance rate : 0.2 [%]

engine maintenance cost per hour : 3666.8 [eur]

wing maintenance cost per hour : 138.2 [eur]

fuselage maintenance cost per hour : 47.56 [eur]

tire life (time till worn out) : 111 [cycles]

maintenance cost per hour (excluding engines): 3386 [eur]

direct operating cost per hour: 17275 [eur], DOC per km : 19.63 [eur]

DOC per seat 1000km flight (367 [pax] 2-class seating): 52.07 [eur/1000PK]

DOC per seat 1000km flight (high density seating): 47.41 [eur/1000PK]

DOC per kg cargo for a 1000km flight : 0.36 [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 : 4.24 [eur/pax]

airport landing fee / passenger : 4.24 [eur/pax]

retour ticket price 1000km trip : 180.36 [eur/pax]

price retour ticket Schiphol-Barcelona : 209.00 [eur/pax]

accidents with fatalities > see the accident file

Literature :

Boeing 787 Dreamliner - Wikipedia

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

KLM Boeing 787-9 PH-BHD parked at Schiphol Oost, 7 November 2023

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 30 October 2024 contact : info.aircraftinvestigation@gmail.com ac jetpax 2020.py python 3.7.4

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