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weight and performance calculations for the Airbus A321-100
***** PRELIMINARY FILE ****
Austrian Airlines A321-111 OE-LBB “Pinzgau” c/n 570 with CFM56-5B1 engines
Airbus A321-100
role : jet airliner
importance : ****
first flight : 11 March 1993 operational : March 1994
country : EU-consortium
design :
production : 90 A321-100 aircraft, total A321 production : status oct.2022 : 2646 aircraft
final assembly in Hamburg, Germany.
general information :
In November 1989, an extended version of the A320 was launched, which has 24% more seats and 40% more cargo space. It was offered with to different engines : the GE-Snecma CFM56-5B or the IAE V2530-5A.
A plug of 4.27m in front of the wing and one of 2.67m behind the wing was inserted, bringing the length to 44.51m. The A321-100 had a shorter range then the A320 due to its heavier weight. Soon it was followed on the production line by the A321-200 which had additional fuel tanks to improve range.
primary users : Lufthansa (19+1), Austrian Airlines (3+2), Air Macau (4), All Nippon Airways (2+5), Asiana (2+10), CAAC (13), Transasia(6), Air Alfa (2+1), Air France (6+1), Alitalia (20+5), Onur Air (4), Swissair (9+3)
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 : 220 passengers
engine : 2 GE-Snecma CFM56-5B1 turbofan engines of 133.4 [KN] (29989.0 [lbf])
or IAE V2530-A5 engines of 133.0 [KN]
dimensions :
wingspan : 34.09 [m], length : 44.51 [m], height : 11.8 [m]
wing area : 122.4 [m^2] fuselage exterior width : 3.95 [m]
weights :
empty weight : 45822 [kg]
operating empty weight : 47700 [kg] max. structural payload : 21800 [kg]
Zero Fuel weight (ZFW) : 69500 [kg] max. landing weight (MLW) : 73500 [kg]
max.take-off weight : 83000 [kg] weight fuel : 19240 [kg] (24050 [liter])
performance :
Max. operating Mach number (Mmo) : 0.84 [Mach] (940 [km/hr]) at 7500 [m]
normal cruise speed : 904 [km/hr] (Mach 0.84 ) at 10000 [m] (27 [%] power)
economic cruise speed : 837 [km/hr] (Mach 0.78 ) at 10000 [m]
service ceiling : 11900 [m]
range with max fuel : 4300 [km] (ATA domestic fuel reserves - 370.0 [km] alternate)
description :
low-wing cantilever monoplane with retractable landing gear with nose wheel
tapered multi-cellular wing with flush-riveted stressed skin
with double slotted flaps with slotted LE flaps (slats) airfoil : Airbus
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 : aluminium-alloy stressed-skin construction with pressurized fuselage combined with composite materials
fuselage shape : 0
calculation : *1* (dimensions)
wing chord at root : 6.07 [m]
mean wing chord : 3.59 [m]
calculated average wing chord tapered wing with rounded tips: 3.57 [m]
wing aspect ratio : 9.49 []
seize (span*length*height) : 17905 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 8.0 [kg/hr]
fuel consumption (econ. cruise speed) : 3448.4 [kg/hr] (4310.5 [litre/hr]) at 21 [%] power
distance flown for 1 kg fuel : 0.24 [km/kg] at 10000 [m] height, sfc : 60.8 [kg/KN/h]
total fuel capacity : 24050 [litre] (19240 [kg])
calculation : *3* (weight)
weight engine(s) dry : 4760.0 [kg] = 17.84 [kg/KN]
weight 65 litre oil tank : 5.55 [kg]
oil tank filled with 1.7 litre oil : 1.5 [kg]
oil in engine 3.3 litre oil : 2.9 [kg]
fuel in engine 14.6 litre fuel : 10.67 [kg]
weight fuel lines 65.3 [kg]
weight engine cowling 693.7 [kg]
weight thrust reversers 106.7 [kg]
total weight propulsion system : 5646 [kg](6.8 [%])
***************************************************************
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 : 220 [pax] at 6 -abreast seating in 36.6 rows, pitch 73.7 [cm]
Lufthansa A321 interior
pax density, normal seating : 0.61 [m2/pax], high density seating : 0.52 [m2/pax]
weight 4 lavatories : 55.7 [kg]
weight 3 galleys : 193.0 [kg]
weight overhead stowage for hand luggage : 65.1 [kg]
weight 4 wardrobe closets : 37.2 [kg]
weight 65 windows : 58.6 [kg]
weight 4 1.83x0.86 [m] entrance/exit doors : 202.6 [kg]
weight 2 freight doors (belly) : 80.4 [kg]
belly baggage/cargo hold volume front : 23.22 [m3]
belly baggage/cargo hold volume rear : 30.16 [m3]
The A321 can take 10 AKH type ULD (unit load device) in it’s belly.
passenger compartment volume : 155 [m3]
passenger cabin max.width : 3.66 [m] cabin length : 34.39 [m] cabin height : 2.18 [m]
floor area : 113.4 [m2]
weight cabin facilities : 1662.6 [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 : 181.8 [kg]
weight safety equipment & facilities : 450 [kg]
fuselage construction:
fuselage aluminium frame : 13724 [kg]
floor loading (payload/m2): 192 [kg/m2]
weight rear pressure bulkhead : 170.5 [kg]
fuselage covering ( 426.5 [m2] duraluminium 2.73 [mm]) : 3059.6 [kg]
weight floor beams : 802.4 [kg]
weight cabin furbishing : 1019.7 [kg]
weight cabin floor : 1460.5 [kg]
fuselage (sound proof) isolation : 308.7 [kg]
8250 litre central tank + 2x 7750 litre wing tanks = 23750 liter total.
Total Fuel with CFM engines : 24050 liter, with IAE engines 23700 liter
weight 8250 [litre] main central fuel tanks empty : 462.0 [kg]
weight empty waste tank : 19 [kg]
weight fuselage structure : 21025.6 [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]
Cockpit of Lufthansa A321-131 D-AIRF
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 5625 [m]
and gives equivalent of 2440 [m] at 10700 [m]. pressure differential : 0.53 [bars] (kg/cm2)
pressurized fuselage volume : 418 [m3]
weight air-conditioning and pressurisation system : 229 [kg]
weight APU / engine starter: 66.7 [kg]
weight lighting : 61.4 [kg]
weight engine-driven 40kVA electricity generators : 46.5 [kg]
weight controls : 18.2 [kg]
weight systems : 421.8 [kg]
total weight fuselage : 23640 [kg](28.5 [%])
***************************************************************
total weight aluminium ribs (1181 ribs) : 2960 [kg]
weight engine mounts : 133 [kg]
weight 6 fuel tanks empty for total 15800 [litre] fuel : 885 [kg]
weight wing covering (painted aluminium 4.70 [mm]) : 3107 [kg]
total weight aluminium spars (multi-cellular wing structure) : 2715 [kg]
weight wings : 8781 [kg]
weight wing/square meter : 71.74 [kg]
weight thermal leading-edge anti-icing : 37.5 [kg]
weight fin & rudder (13.5 [m2]) : 969.8 [kg]
weight stabilizer & elevator (13.8 [m2]): 988.8 [kg]
weight flight control hydraulic servo actuators: 64.7 [kg]
weight double slotted flaps (20.7 [m2]) : 635.8 [kg]
weight leading edge slats (6.6 [m2]) : 134.5 [kg]
total weight wing surfaces & bracing : 12631 [kg] (15.2 [%])
*******************************************************************
tyre pressure main wheels : 13.60 [Bar] (nitrogen), ply rating : 23 PR
Can only operate from paved runways
wheel pressure : 18260.0 [kg]
weight 4 Dunlop main wheels (1240 [mm] by 455 [mm]) : 838.5 [kg]
weight 2 nose wheels : 209.6 [kg]
weight multi-disc wheel-brakes : 69.5 [kg]
weight flywheel detector type anti-skid units : 5.4 [kg]
weight oleo-pneumatic shock absorbers : 92.7 [kg]
weight wheel hydraulic operated retraction system : 893.7 [kg]
weight undercarriage struts with axle 2314.4 [kg]
total weight landing gear : 4423.7 [kg] (5.3 [%]
*******************************************************************
********************************************************************
calculated empty weight : 46341 [kg](55.8 [%])
weight oil for 5.7 hours flying : 53.6 [kg]
weight catering : 321.7 [kg]
weight water : 257.4 [kg]
weight crew : 648 [kg]
weight crew lugage,nav.chards,flight doc.,miscell.items : 78 [kg]
operational weight empty : 47700 [kg] (57.5 [%])
********************************************************************
weight 186 passengers : 14322 [kg]
weight luggage : 2976 [kg]
weight cargo : 4502 [kg]
zero fuel weight (ZFW): 69500 [kg](83.7 [%])
weight fuel for landing (1.2 hours flying) : 4000 [kg]
max. landing weight (MLW): 73500 [kg](88.6 [%])
max. fuel weight : 66940 [kg] (80.7 [%])
payload with max fuel : 173 passengers+luggage 16060 [kg]
published maximum take-off weight : 83000 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 311 [kg/KN]
power loading (Take-off) 1 PUF: 622 [kg/KN]
max. total take-off power : 266.8 [KN]
calculation : *5* (loads)
manoeuvre load : 4.3 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 1.3 [g]
design flight time : 3.46 [hours]
design cycles : 27518 sorties, design hours : 95193 [hours]
max. wing loading (MTOW & flaps retracted) : 678 [kg/m2]
wing stress (2 g) during operation : 174 [N/kg] at 2g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.68 ["]
max. angle of attack (stalling angle, clean) : 11.01 ["]
max. angle of attack (full flaps) : 10.21 ["]
angle of attack at max. speed : 2.02 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.33 [ ]
lift coefficient at max. angle of attack : 1.13 [ ]
Lufthansa Airbus A321-131 c/n 560 taking off, IAE V2530-A5 engines.
max. lift coefficient full flaps : 1.63 [ ]
drag coefficient at max. speed : 0.0341 [ ]
drag coefficient at econ. cruise speed : 0.0415 [ ]
induced drag coefficient at econ. cruise speed : 0.0123 [ ]
drag coefficient (zero lift) : 0.0292 [ ]
lift/drag ratio at max. speed : 9.70 [ ]
calculation : *8* (speeds
stalling speed clean at sea-level (OW loaded : 79552 [kg]): 345 [km/u]
stalling speed at sea-level with full flaps (normal landing weight): 250 [km/u]
landing speed at sea-level (normal landing weight : 73210 [kg]): 287 [km/hr]
approach speed at sea-level with full flaps (normal landing weight): 324 [km/u]
max. rate of climb speed : 683 [km/hr] at sea-level
max. endurance speed : 665 [km/u] min. fuel/hr : 3151 [kg/hr] at height : 9754 [m]
max. range speed : 939 [km/u] min. fuel consumption : 3.783 [kg/km] at cruise height : 11278 [m]
cruising speed : 904 [km/hr] at 10000 [m] (power:23 [%])
max. operational speed (Mmo) : 940.00 [km/hr] (Mach 0.84 ) at 7500 [m] (power:29.1 [%])
airflow at cruise speed per engine : 243.6 [kg/s]
speed of thrust jet : 1354 [km/hr]
climbing speed at sea-level (loaded) : 2051 [m/min]
climbing speed at 1000 [m] with 1 engine out (PUF / MTOW) : 698 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 368.2 [km/u]
high wheel pressure, can only take off from paved runways
take-off distance at sea-level concrete runway : 2683 [m]
take-off distance at sea-level over 15 [m] height : 2766 [m]
landing run : 1792 [m]
landing run (C.A.R.) from 15 [m] at SL, dry runway : 2484 [m]
landing run (C.A.R.) from 15 [m] at SL, wet runway : 2784 [m]
lift/drag ratio : 13.88 [ ]
climb to 5000 [m] with max payload : 2.23 [min]
climb to 10000 [m] with max payload : 3.74 [min]
theoretical ceiling fully loaded (mtow- 60 min. fuel:79552 [kg] ) : 14100 [m]
calculation *10* (action radius & endurance)
range with max. payload: 3201 [km] with 21800.0 [kg] max. useful load (70.2 [%] fuel)
range with high density pax: 3543 [km] with 220 passengers (77.2 [%] fuel)
range with typical two-class pax: 4348 [km] with 186 passengers (93.6 [%] fuel)
range with max.fuel : 4670 [km] with 8 crew and 173 passengers and 100.0 [%] fuel
ferry range : 5321 [km] with 2 crew and zero payload (100.0 [%] fuel)
max range theoretically with additional fuel tanks total 45456.3 [litre] fuel : 9443 [km]
Available Seat Kilometres (ASK) : 808661 [paskm]
useful load with range 1000km : 21800 [kg]
useful load with range 1000km : 220 passengers
production (theor.max load): 19707 [tonkm/hour]
production (useful load): 19707 [tonkm/hour]
production (passengers): 168144 [paskm/hour]
oil and fuel consumption per tonkm : 0.175 [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 : 0.010 [eur]
insurance per paskm : 0.0008 [eur]
maintenance cost per paskm : 0.014 [eur]
direct operating cost per paskm : 0.052 [eur]
direct operating cost per tonkm (max. load): 0.444 [eur]
direct operating cost per tonkm (normal useful load): 0.444 [eur]
On 02 February 2016 Airbus A321-111, SX-BHS c/n 642 leased from Hermes Airlines, operating Daallo Airlines flight D3 159, suffered an in-flight explosion about 15 minutes after takeoff from Mogadishu Airport, Somalia when the aircraft was at about 12,000 feet. The explosion occurred on the right hand side of the aircraft, just behind the R2 door, at or around seat 16F. A large hole was blown in the fuselage and one passenger fell out of the aircraft and was killed. Two other passengers were injured. CFM56-5B1 engines.
The aircraft returned to Mogadishu where it landed safely at 08:53 UTC (11:53 hours local time). This was the only fatal accident involving an A321-100.
Location : +- 3km : 2°21’00”N 45°27’48”E
Literature :
luchtvaart sept’90 page 256, 257
Air international dec’97 page 383
Jane's all the world aircraft ‘90-’91
Flugrevue june’97 page 9
Flight international 18/24 nov’98 page 45
Aircraft Characteristics | Airbus
https://contentzone.eurocontrol.int/aircraftperformance/default.aspx ?
The only hull loss so far concerns the A321-131 B-22603 from Transasia.
On 21 March 2003 it collides with a airport service vehicle when landing at RW36R of Tainan (TNN), Taiwan. The 170 passengers and 5 crew members remained unharmed. V2530-A5 engines. Location : +-300m 22°57'09"N 120°12'28"E
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