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weight and performance calculations for the Boeing 787-8
***** PRELIMINARY FILE ****
Boeing 787-8 Dreamliner
role : wide-body airliner
importance : ****
first flight : operational : October 2011
country : United States of America
design :
production : 377 aircraft
general information :
Max cargo lower deck : 136.7 [m3]
primary users : ANA, TUI
flight crew : 2 cabin crew : 8 passengers : 242 (20 business + 222 econ.class),
359 all-economy 1-class (FAA exit limit : 381 seats)
engine : 2 Rolls Royce Trent 1000 turbofan engines of 280.0 [KN](62945.4 [lbf])
dimensions :
wingspan : 60.12 [m], length : 56.72 [m], height : 16.92 [m]
wing area : 377.0 [m^2]
weights :
operating empty weight : 119950 [kg] max. structural payload : 41075 [kg]
Zero Fuel weight (ZFW) : 161025 [kg] max. landing weight (MLW) : 172365 [kg]
max.take-off weight : 227930 [kg] weight fuel : 100965 [kg] (126206 [liter])
performance :
Max. operating Mach number (Mmo) : 0.89 [Mach] (956 [km/hr]) at 10000 [m]
normal cruise speed : 903 [km/hr] (Mach 0.85 ) at 11000 [m] (36 [%] power)
service ceiling : 13100 [m]
range with max fuel : 13620 [km] and allowance for 1713.3 [km] diversion and
30 [min] hold
description :
low-wing cantilever monoplane with retractable landing gear with nose wheel
tapered multi-cellular wing with flush-riveted stressed skin
with Fowler flaps airfoil : NACA
sweep angle 3/4 chord: 31.6 [°]
engines attached with pylons to the wing, main landing gear attached to the wings, fuel
tanks in the wings and fuselage
construction : CFRP (carbon fiber reinforced polymer) stressed-skin construction with pressurized fuselage
fuselage shape : 0
calculation : *1* (dimensions)
mean wing chord : 6.27 [m]
calculated average wing chord tapered wing with rounded tips: 6.12 [m]
wing aspect ratio : 9.59 []
seize (span*length*height) : 57697 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 56.0 [kg/hr]
fuel consumption (econ. cruise speed) : 5898.3 [kg/hr] (7372.9 [litre/hr]) at 36 [%]
power
distance flown for 1 kg fuel : 0.15 [km/kg] at 11000 [m] height, sfc : 29.3 [kg/KN/h]
total fuel capacity : 126206 [litre] (100965 [kg])
calculation : *3* (weight)
weight engine(s) dry : 12000.0 [kg] = 21.43 [kg/KN]
weight 1140.8 litre oil tank : 96.97 [kg]
oil tank filled with 3.5 litre oil : 3.2 [kg]
oil in engine 93.6 litre oil : 84.0 [kg]
fuel in engine 68.8 litre fuel : 50.40 [kg]
weight fuel lines 126.2 [kg]
weight engine cowling 1680.0 [kg]
total weight propulsion system : 14041 [kg](6.2 [%])
***************************************************************
fuselage composite (carbon) frame : 33015 [kg]
typical cabin layout for 242 passengers : average pitch : 81 [cm] ( 3+3+3 ) seating in
26.9 rows
pax density (normal seating) : 0.89 [m2/pax]
high density seating passengers : 378 at 9 -abreast seating in 42.0 rows, pitch 81 [cm]
weight 7 toilets : 105.7 [kg]
weight 12 hand fire extinguisher : 36 [kg]
weight 5 galleys : 511.0 [kg]
weight overhead stowage for hand luggage : 84.7 [kg]
weight 2 closets : 24.2 [kg]
weight 2 movie screens : 48.4 [kg]
weight 56 windows : 50.2 [kg]
weight 2 overwing emergency exits : 7.4 [kg]
weight lifejackets : 108.9 [kg]
weight oxygen masks & oxygen generators : 157.3 [kg]
weight emergency flare installation : 10 [kg]
weight 4 emergency evacuation slides : 104.7 [kg]
weight 4 entrance/exit doors : 48.0 [kg]
weight 2 freight doors (belly) : 8.0 [kg]
cabin volume (usable), excluding flight deck : 922.17 [m3]
passenger cabin max.width : 5.52 [m] cabin length : 43.10 [m] cabin height : 2.18 [m]
floor area : 214.4 [m2]
pressure at cruise height 12192.00 [m] : 0.19 [kg/cm2] cabin pressure : 0.77 [kg/cm2]
weight rear pressure bulkhead : 487.1 [kg]
weight air pressurization system : 129.7 [kg]
fuselage covering ( 800.2 [m2] CFRP 3.42 [mm]) : 7309.4 [kg]
weight floor beams : 4202.6 [kg]
weight cabin furbishing : 1882.4 [kg]
weight cabin floor : 2041.2 [kg]
fuselage (sound proof) isolation : 587.3 [kg]
weight radio transceiver equipment : 7.0 [kg]
weight dual cloud-collision radar : 25.0 [kg]
weight radio direction finding (RDF) equipment : 5.0 [kg]
weight Sperry Integrated Flight System : 11.0 [kg]
weight artificial horizon : 1.1 [kg]
weight instruments. : 36.0 [kg]
weight APU / engine starter: 140.0 [kg]
weight lighting : 60.5 [kg]
weight electricity generator : 60.5 [kg]
weight controls : 23.7 [kg]
weight seats : 1260.0 [kg]
weight 63103 [litre] main central fuel tanks empty : 3533.8 [kg]
weight air conditioning : 363 [kg]
total weight fuselage : 55797 [kg](24.5 [%])
***************************************************************
total weight carbon ribs (1857 ribs) : 8128 [kg]
weight engine mounts : 280 [kg]
weight fuel tanks empty for total 63103 [litre] fuel : 3534 [kg]
weight wing covering (painted carbon 2.78 [mm]) : 5658 [kg]
total weight carbon spars (multi-cellular wing structure) : 12628 [kg]
weight wings : 26414 [kg]
weight wing/square meter : 70.06 [kg]
weight rubber de-icing boots : 66.1 [kg]
weight fin & rudder (42.0 [m2]) : 2945.7 [kg]
weight stabilizer & elevator (42.4 [m2]): 2974.4 [kg]
weight flight control hydraulic servo actuators: 196.4 [kg]
weight fowler flaps (23.9 [m2]) : 842.3 [kg]
total weight wing surfaces & bracing : 37253 [kg] (16.3 [%])
*******************************************************************
wielen naar verhouding erg licht
wheel pressure : 16714.9 [kg]
weight 8 Dunlop main wheels (1130 [mm] by 226 [mm]) : 1496.8 [kg]
weight 2 Dunlop nose wheels : 124.7 [kg]
weight hydraulic wheel-brakes : 161.0 [kg]
weight pneumatic-hydraulic shock absorbers : 214.7 [kg]
weight wheel hydraulic operated retraction system : 1752.1 [kg]
weight undercarriage struts with axle 4923.7 [kg]
total weight landing gear : 8673.0 [kg] (3.8 [%]
*******************************************************************
********************************************************************
calculated empty weight : 115764 [kg](50.8 [%])
weight oil for 18.1 hours flying : 1013.6 [kg]
weight catering : 1277.5 [kg]
weight water : 1022.0 [kg]
weight crew : 810 [kg]
weight crew lugage,nav.chards,flight doc.,miscell.items : 63 [kg]
operational weight empty : 119950 [kg] (52.6 [%])
TUI 787-8 layout for 305 pax
********************************************************************
weight 242 passengers : 18634 [kg]
weight luggage : 2952 [kg]
weight cargo : 19489 [kg]
zero fuel weight (ZFW): 161025 [kg](70.6 [%])
weight fuel for landing (1.9 hours flying) : 11340 [kg]
max. landing weight (MLW): 172365 [kg](75.6 [%])
max. fuel weight : 220915 [kg] (96.9 [%])
payload with max fuel : 79 passengers+luggage 7015 [kg]
published maximum take-off weight : 227930 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 407 [kg/KN]
power loading (operational without useful load) : 357 [kg/kN]
power loading (Take-off) 1 PUF: 814 [kg/KN]
max. total take-off power : 560.0 [KN]
calculation : *5* (loads)
manoeuvre load : 7.2 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 0.9 [g]
design flight time : 10.56 [hours]
design cycles : 2621 sorties, design hours : 27669 [hours]
operational wing loading : 5191 [N/m^2]
wing stress (3 g) during operation : 222 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.67 ["]
max. angle of attack (stalling angle, clean) : 12.90 ["]
angle of attack at max. speed : 2.32 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.36 [ ]
lift coefficient at max. angle of attack : 1.31 [ ]
max. lift coefficient full flaps : 1.58 [ ]
induced drag coefficient at max.speed : 0.0055 [ ]
drag coefficient at max. speed : 0.0421 [ ]
drag coefficient (zero lift) : 0.0366 [ ]
lift/drag ratio at max. speed : 8.49 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 222032 [kg]): 306 [km/u]
stalling speed at sea-level with full flaps (normal landing weight): 245 [km/u]
landing speed at sea-level (normal landing weight : 171215 [kg]): 281 [km/hr]
max. rate of climb speed : 550 [km/hr] at sea-level
max. endurance speed : 513 [km/u] min. fuel/hr : 4057 [kg/hr] at height : 8534 [m]
max. range speed : 785 [km/u] min. fuel consumption : 5.967 [kg/km] at cruise height : 10973 [m]
cruising speed : 903 [km/hr] at 11000 [m] (power:32 [%])
max. operational speed (Mmo) : 956.00 [km/hr] (Mach 0.89 ) at 10000 [m] (power:40.2 [%])
airflow : 1164.7 [kg/s]
speed of thrust jet : 1525 [km/hr]
climbing speed at sea-level (loaded) : 1550 [m/min]
climbing speed at 1000 [m] with 1 engine out (PUF / MTOW) : 1291 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 371.9 [km/u]
high wheel pressure, can only take off from paved runways
take-off distance at sea-level concrete runway : 2235 [m]
take-off distance at sea-level over 15 [m] height : 2324 [m]
landing run : 1553 [m]
landing run from 15 [m] : 2546 [m]
lift/drag ratio : 12.58 [ ]
max. theoretical ceiling : 17000 [m] with flying weight :222032 [kg] line 3359
climb to 1000m with max payload : 0.72 [min]
climb to 2000m with max payload : 1.40 [min]
climb to 3000m with max payload : 2.05 [min]
climb to 5000 [m] with max payload : 3.22 [min]
minimum flying speed at 13100 [m] : 741 [km/hr]
theoretical ceiling fully loaded (mtow- 60 min. fuel:222032 [kg] ) : 17000 [m]
calculation *10* (action radius & endurance)
published range : 13620 [km] with 10 crew and 19015 [kg] useful load and 96.2 [%]
fuel
range : 10243 [km] with 10 crew and 41075.0 [kg] useful load and 72.3 [%] fuel
range : 13226 [km] with 242.0 passengers with each 12.2 [kg] luggage and 93.4 [%]
fuel
range max. fuel : 15457 [km] with 7015 [kg] useful load and 100.0 [%] fuel
Available Seat Kilometres (ASK) : 3200782 [paskm]
max range theoretically with additional fuel tanks total 134975.0 [litre] fuel : 18098
[km]
useful load with range 500km : 104714 [kg]
useful load with range 500km : 242 passengers
production (theor.max load): 94557 [tonkm/hour]
production (useful load): 37091 [tonkm/hour]
production (passengers): 218526 [paskm/hour]
combi aircraft mail/freight/passengers
oil and fuel consumption per tonkm : 0.063 [kg]
fuel cost per paskm : 0.027 [eur]
crew cost per paskm : 0.006 [eur]
time between engine failure : 932 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
writing off per paskm : 0.016 [eur]
insurance per paskm : 0.0005 [eur]
maintenance cost per paskm : 0.053 [eur]
direct operating cost per paskm : 0.103 [eur]
direct operating cost per tonkm (max. load): 0.238 [eur]
direct operating cost per tonkm (normal useful load): 0.607 [eur]
Literature :
wikipedia
Front Matter Template 5.0 (boeing.com)
Aircraft Performance Database > B788 (eurocontrol.int)
http://www.aircraftmonitor.com/uploads/1/5/9/9/15993320/aircraft_payload_range_analysis_for_financiers___v2.pdf
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 27 June 2022 contact : info.aircraftinvestigation@gmail.com python 3.7.4