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weight and performance calculations for the Airbus A320-200 V2500
EgyptAir A320-231 SU-GBF c/n 351 “Sharm el Sheikh” with IAE V2500-A1 engines May 2000 © bvdz
Airbus A320-200 V2500
role : jet airliner
importance : ****
first flight : 28 July 1988 operational : May 1989 (Adria Airlines)
country : EU-consortium
ICAO aircraft type designator : A320
production : 4752 aircraft, estimation 35% has V2500 engines = 1663
general information :
The A320-200 was offered with 2 different engines, the CFM56-5A1 and the IAE
V2500-A1.
primary users : British Caledonian, Adria Airlines, Cyprus Airways, American Airlines,
Easyjet, Indigo, Egypt Air.
Accommodation:
flight crew : 2 cabin crew : 5
passengers : seating for 150 in two class : 12 business class and 138 economy class seats
( 32 -in pitch) high density seating for max 180 passengers (equal to exit limit)
engine : 2 IAE V2500-A1 turbofan engines of 111.2 [KN] (24998 [lbf])
dimensions :
wingspan : 34.1 [m], length overall: 37.57 [m], length of fuselage : 37.57 [m] height :
11.76 [m] wing area gross : 122.4 [m^2] fuselage exterior width : 3.95 [m]
weights :
operating empty weight : 41640 [kg] max. structural payload : 18860 [kg]
Zero Fuel weight (ZFW) : 60500 [kg] max. landing weight (MLW) : 64500 [kg]
max. take-off weight : 73500 [kg] weight usable fuel : 18729 [kg] (23859 [litres])
performance :
Max. operating Mach number (Mmo) : 0.822 [Mach] (884 [km/hr]) at 10000 [m]
critical Mach speed : 0.78 [Mach]
max. cruising speed : 870 [km/hr] (Mach 0.81 ) at 10000 [m] (31 [%] power)
economic cruising speed : 837 [km/hr] (Mach 0.78 ) at 10000 [m]
service ceiling : 11900 [m]
range with max fuel and MTOW : 5850 [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 : two main spar fail-safe wing structure with double slotted trailing edge flaps
with full-span slotted LE flaps (slats) ,with spoilers and airbrakes and with wingtip
fences. airfoil : Airbus, average thickness/chord ratio : 10.0 [%], sweep angle 3/4 chord:
25.0 [°] incidence at root : 3.00 [°], dihedral : 5.2 [°]
*Fuselage : Pressurized aluminium-alloy stressed-skin structure of elliptical 0 section
British Caledonian A320-231 G-BVYC c/n 411
calculation : *1* (dimensions)
wing chord at root : 6.07 [m]
measured wing chord at tip : 1.62 [m]
taper ratio : 0.267 [ ]
mean wing chord : 3.59 [m]
wing aspect ratio : 9.50 []
Oswald factor (e): 0.704 []
seize (span*length*height) : 15066 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 0.7 [kg/hr]
fuel consumption (econ. cruise speed) : 2520.3 [kg/hr] (3210.6 [litre/hr]) at 20 [%] power
distance flown for 1 kg fuel : 0.33 [km/kg] at 10000 [m] height, sfc : 57.2 [kg/KN/h]
total fuel capacity : 23859 [litre] (18729 [kg])
calculation : *3* (weight)
Adria Airbus A320-231 at Schiphol © bvdz
weight engine(s) dry : 4808.0 [kg] = 21.62 [kg/KN]
weight 11.3 litre oil tank : 0.96 [kg]
oil tank filled with 1.4 litre oil : 1.3 [kg]
oil in engine 2.7 litre oil : 2.4 [kg]
weight all fuel lines and pumps containing 72 litres fuel : 45.1 [kg]
weight engine cowling : 578.2 [kg]
weight thrust reversers : 333.6 [kg]
total weight propulsion system : 5770 [kg](7.8 [%])
***************************************************************
Accommodation cabin facilities:
typical 2-class cabin layout for 150 passengers : economy : pitch : 81.3 [cm] 32.0 [-in]
( 3+3 ) seating in 26.0 rows, business class pitch : 91.4 [cm] 36.0 [-in] at 4 -abreast
weight passenger seats (width 53.7 [cm]) : 748.0 [kg]
weight cabin crew seats : 25.0 [kg]
weight flight crew seats : 42.0 [kg]
high density seating passengers : 180 [pax] at mainly 6 -abreast seating in 31.0 rows,
pitch 73.7 [cm] 29.0 [-in]
pax density, normal seating : 0.678 [m2/pax], high density seating : 0.565 [m2/pax]
weight 3 lavatories : 81.1 [kg]
weight 3 galleys : 123.0 [kg]
Inside EgyptAir A320 SU-GBF
weight overhead stowage for hand luggage (total : 8.4 [m3] = 174 55x35x25cm carry-on
trolleys) : 130.6 [kg]
weight 54 windows (47x38cm) made of acrylic glass: 229.5 [kg]
weight 4 (1.85 x 0.81 [m]) main entry doors : 159.8 [kg]
weight 2 (main door size : 1.25 x 1.82 [m]) freight doors (belly) : 131.9 [kg]*
total usable belly baggage/cargo hold volume : 37.4 [m3]
cabin volume (usable), excluding flight deck : 198 [m3]
passenger compartment volume : 139 [m3]
passenger cabin max width : 3.70 [m] cabin length : 27.50 [m] max cabin height : 2.22
[m] floor area : 92.4 [m2]
weight cabin facilities : 1670.9 [kg]
safety facilities:
weight 4 type III over wing emergency exits (0.51 x 1.02 [m]): 60.3 [kg]
evacuation time with 180 passengers : 45 [sec]
weight 4 hand fire extinguisher : 11 [kg]
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators (deploy cabin alt.>4267m): 97.5 [kg]
weight emergency flare installation : 10 [kg]
weight 4 emergency evacuation slides : 134.7 [kg]
weight safety equipment & facilities : 334 [kg]
fuselage construction:
fuselage aluminium frame : 8202 [kg]
floor loading (payload/m2): 204 [kg/m2]
weight rear pressure bulkhead : 166.4 [kg]
fuselage covering ( 353.8 [m2] duraluminium 2.60 [mm]) : 2417.5 [kg]
weight paint fuselage : 74.3 [kg]
weight aluminium floor beams : 549.4 [kg]
weight cabin furbishing : 852.9 [kg]
weight cabin floor : 1306.4 [kg]
weight (sound proof) isolation : 273.7 [kg] TO-noise level : 97.2 [EPNdB]
weight 7900 [litre] main central fuel tank empty : 158.0 [kg]
weight empty 188 [litre] potable water tanks : 16.6 [kg]
weight empty waste tank : 9.3 [kg]
weight fuselage structure : 14026.3 [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]
Danish Air Transport Airbus A320-231 OY-RUS c/n 447 cockpit
weight VOR/ILS,RMI,DME,radio altimeter, ASI, time clock : 20.0 [kg]
weight Cat IIIB auto-landing system : 10.0 [kg]
weight EFIS (4 Rockwell Collins CRT screens ADI/PFD+HSI/ND displays) : 20 [kg]
weight ground proximity warning system (GPWS) : 6 [kg]
weight engine monitoring system ECAM : 24 [kg]
weight EICAS + 1 LCD display : 18 [kg]
weight reserve ADI, ASI, alti-meter, compass, engine temp. and rpm indicators : 15 [kg]
weight avionics : 138.0 [kg]
Systems:
Air-conditioning and pressurization system maintains sea level conditions up to 6400 [m]
and gives equivalent of 2440 [m] at 12200 [m]. pressure differential : 0.58 [bar] (kg/cm2)
pressurized fuselage volume : 330 [m3] cabin air refreshment time : 2.9 [min]
weight air-conditioning and pressurization system : 191 [kg]
weight APU / engine starter : 55.6 [kg]
weight lighting : 49.5 [kg]
weight 207 bar hydraulic system : 75.3 [kg]
weight engine-driven 40kVA electricity generators : 37.5 [kg]
weight ram air turbine for emergency electric power : 5.0 [kg]
weight 22Ah battery : 28.5 [kg]
weight controls (sidestick FBW): 10.7 [kg]
weight systems : 447.7 [kg]
total weight fuselage : 16616 [kg](22.6 [%])
***************************************************************
total weight aluminium ribs (40 ribs) : 2526 [kg]
weight engine mounts : 111 [kg]
weight 4 wing fuel tanks empty for total 15959 [litre] fuel : 239 [kg]
weight 95 [litre] vent surge tanks : 11 [kg]
weight wing covering (painted aluminium 5.80 [mm]) : 3833 [kg]
total weight aluminium spars (multi-cellular wing structure) : 2840 [kg]
weight wings : 9200 [kg]
weight wing/square meter : 75.16 [kg]
weight bleed air thermal leading-edge anti-icing : 37.5 [kg]
weight ailerons (2.7 [m2]) : 82.6 [kg]
weight fin (16.3 [m2]) : 613.8 [kg]
weight rudder (5.2 [m2]) : 187.7 [kg]
weight tailplane (horizontal stabilizer) (24.8 [m2]): 1028.6 [kg]
weight elevators (6.2 [m2]): 125.2 [kg]
weight paint wing & tail surfaces : 68.7 [kg]
weight flight control hydraulic servo actuators: 25.1 [kg]
weight trailing-edge double slotted flaps (21.1 [m2]) : 680.0 [kg]
weight leading edge slats (12.6 [m2]) : 264.4 [kg]
weight aluminium honeycomb spoilers (8.6 [m2]) : 151.8 [kg]
weight airbrakes (2.4 [m2]) : 49.6 [kg]
weight wingtip fences : 50 [kg]
total weight wing construction : 13077 [kg] (31.4 [%])
*******************************************************************
tire pressure main wheels : 11.80 [Bar] (nitrogen), ply rating : 23 PR
tire speed limit : 364 [km/hr]
total tyre footprint : 0.39 [m2]
Runway LCN at MTOW (0.76m radius of rigidity) : 49 [ ]
Aircraft Classification Number (ACN), MTOW on rigid runway and medium subgrade
strength (B) : 30 [ ] Can also operate from unpaved runways subgrade B
wheel pressure : 16170.0 [kg]
wheel track : 7.59 [m] wheelbase : 12.64 [m]
weight 4 Dunlop 49.0 x 18.0 main wheels (1245 [mm] by 457 [mm]) : 544.0 [kg]
weight 2 nose wheels : 136.0 [kg]
weight multi-disc wheel-brakes : 71.2 [kg]
weight Hydro-air flywheel detector type anti-skid units : 5.4 [kg]
weight oleo-pneumatic shock absorbers : 80.7 [kg]
weight wheel hydraulic operated retraction system : 1000.5 [kg]
weight undercarriage struts with axle 3114.9 [kg]
total weight landing gear : 4952.7 [kg] (6.7 [%]
*******************************************************************
Indian Airlines had 31 A320-231’s with 4-wheel bogie landing gear for lower runway loads, here VT-ESL c/n 499 comes in for landing at Bangaluru, India , April 2009
********************************************************************
calculated empty weight : 40416 [kg](55.0 [%])
weight oil for 8.1 hours flying : 5.9 [kg]
unusable fuel in engine and tanks 95.4 litre fuel : 74.9 [kg]
weight lifejackets : 67.5 [kg]
weight 3 life rafts : 93.8 [kg]
weight catering : 120.4 [kg]
weight water : 166.1 [kg]
weight crew : 567 [kg]
weight crew luggage, navigation chards, flight docs (NOTOC), manuals, miscellaneous
items : 129 [kg]
operational weight empty : 41640 [kg] (56.7 [%])
********************************************************************
weight 150 passengers : 11550 [kg]
weight luggage : 2400 [kg]
weight cargo : 4910 [kg] (cargo + luggage/m3 belly : 160 [kg/m3])
zero fuel weight (ZFW): 60500 [kg](82.3 [%])
weight fuel for landing (1.6 hours flying) : 4000 [kg]
max. landing weight (MLW): 64500 [kg](87.8 [%])
max. fuel weight : 60369 [kg] (82.1 [%])
payload with max fuel : 141 passengers + luggage 13131 [kg]
published maximum take-off weight : 73500 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 330 [kg/KN]
power loading (Take-off) 1 PUF: 661 [kg/KN]
max. total take-off power : 222.4 [KN]
calculation : *5* (loads)
manoeuvre load : 0.9 [g] at 9000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.8 [g]
design flight time : 2.05 [hours]
design cycles : 31875 sorties, design hours : 65344 [hours]
max. wing loading (MTOW & flaps retracted) : 600 [kg/m2]
wing stress (2 g) during operation : 147 [N/kg] at 2g emergency manoeuvre
Indigo A320-232 VT-IES c/n 5090 at Dubai apt. (DXB), January 2013. Indigo has a fleet of 267 A320’s
calculation : *6* (angles of attack)
angle of attack zero lift : -1.69 ["]
max. angle of attack (stalling angle, clean) : 12.14 ["]
max. angle of attack (full flaps) : 19.88 ["]
angle of attack at economic cruise speed : 3.49 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.44 [ ]
lift coefficient at max. angle of attack (clean): 1.23 [ ]
max. lift coefficient 50 [° ] flap setting : 2.31 [ ]
drag coefficient at max. speed : 0.0350 [ ]
drag coefficient at econ. cruise speed : 0.0323 [ ]
induced drag coefficient at econ. cruise speed : 0.0101 [ ]
drag coefficient (zero lift) : 0.0222 [ ]
lift/drag ratio at econ. speed : 12.70 [ ]
calculation : *8* (speeds
minimum control speed (Vmc) equal to V1
minimum unstick speed (Vmu) at TO angle 14.5 ° : 267 [km/u] (144 [kt])
take-off decision speed (V1) : 262 [km/u] (142 [kt])
take-off rotation speed (VR) : 275 [km/u] (149 [kt])
lift-off speed (VLOF) : 304 [km/u] (164 [kt]) at pitch angle : 10.9 [°]
American airlines is the largest A320 operator with 467 aircraft in its inventory. Here is taking off Airbus A320-232 N651AW c/n 866 from Fort Lauderdale, February 2019. It has IAE V2527-A5 engines. American airlines flies also with A320-200’s with CFM56 engines.
take-off safety speed (V2) : 307 [km/u] (166 [kt])
flap retraction speed (V3) at 500m (OW loaded : 70980 [kg]): 336 [km/u] (182 [kt])
steady initial climb speed (V4) : 333 [km/u] (180 [kt])
climb speed (to FL150 with 66 [%] power) : 636 [km/hr] (343 [kt])
max. endurance speed (Vbe): 703 [km/u] min. fuel/hr : 2338 [kg/hr] at height : 10363 [m]
max. range speed (Vbr): 820 [km/u] (0.78 [mach]) min. fuel consumption : 2.88 [kg/km] at cruise height : 11582 [m]
max. cruising speed : 870 [km/hr] (470 [kt]) at 10000 [m] (power:22 [%])
max. operational speed (Mmo) : 884 [km/hr] (Mach 0.82 ) at 10000 [m] (power:23 [%])
airflow at cruise speed per engine : 203.1 [kg/s]
speed of thrust jet : 1303 [km/hr]
initial descent speed 10000 - 7315 [m]: Mach 0.75
descent speed 7315 - 3048 [m]: 537 [km/u] (290 [kt])
approach speed 3048 - 500 [m] (clean): 463 [km/u] (250 [kt])
minimum control speed (MCS) Vmca (clean): 366 [km/u] (198 [kt])
stalling speed clean at 500 [m] height at Max.Landing Weight : 64500 [kg]): 305 [km/u]
(165 [kt])
Cyprus Airways A320-231 5B-DBC “Tefkros” c/n 295
final approach speed (landing speed) at sea-level with 50 [°] flaps VREF (max. landing
weight): 250 [km/u] (135 [kt])
ICAO Aircraft Approach Category (APC) : C
stalling speed at sea-level with full flaps VSO (max. landing weight): 192 [km/u] (104 [kt]
rate of climb (max. continuous power) at sea-level ROC (loaded, 66 % power) : 1330
[m/min]
rate of climb at sea-level ROC (loaded, 75 % power) : 1664 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 66 % power on remaining engines) : 235 [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)
low wheel pressure, can also take off from unpaved runways
take-off distance at sea-level gravel/packed earth field : 1953 [m]
Brake kinetic energy capacity : 1878 [KW]
Take-off field length at MTOW 73500 kg (162037 lb), at s/l, standard day, dry runway : 6200 ft > 1890m Jane’s 1991-92 +15° : 2300m, Wikipedia : 2100m, eurocontrol : 2190m , average : 2095m calculated : 2061m
FAR TO runway length (TOFL) requirement at TOW 73500 [kg] standard day at SL
(PUF after V1): 2060 [m]
Take-off flap setting : 10 [° ]
+++ FAA certification landing distance : +++
landing weight : 64500 [kg], TE flap setting : 50 [°]
runway condition : dry , landing over 50ft (15m) at threshold at sea-level
with use of thrust reversers, glideslope : 3.5 [°]
Landing field length at MWL 64500 kg (142195 lb), at s/l, dry runway : 4700 ft > 1435 m
FAA approved landing field length at SL, dry runway : 1462 [m] (4798 [ft])
FAA approved landing field length at SL, wet runway: 1672 [m] (5486 [ft])
max. lift/drag ratio : 15.39 [ ]
climb to 5000 [m] with max payload : 3.48 [min]
climb to 10000 [m] with max payload : 10.70 [min]
descent time from 10000 [m] to 250 [m] : 24.33 [min]
max. ceiling fully loaded (mtow- 60 min.fuel): 70980 [kg] ) : 14900 [m]
ceiling limited by max. pressure differential 14125 [m]
max. theoretical ceiling (OWE + 60 min.fuel) : 17400 [m] with flying weight :44160 [kg]
calculation *10* (action radius & endurance)
range with max. payload: 4197 [km] with 18860.0 [kg] max. useful load (69.4 [%] fuel)*
range with high density pax: 4933 [km] with 180 passengers (80.7 [%] fuel)*
range with typical two-class pax: 5924 [km] with 150 passengers (95.6 [%] fuel)*
With wingtip fences
Range with max payload : 1725nm > 3195 km
Range with max fuel : 3700nm > 6850 km
Ferry range : 4300nm > 7965 km
...
range with max.fuel and MTOW : 6220 [km] with 7 crew and 141 passengers and 0
[kg] cargo*
ferry range (calculated): 7072 [km] with 2 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 41467 [litre] fuel : 11548 [km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 888259 [paskm]
useful load with range 1000km : 18860 [kg]
useful load with range 1000km : 180 passengers
production (theor.max load): 16408 [tonkm/hour]
production (useful load): 16408 [tonkm/hour]
production (passengers): 130157 [paskm/hour]
oil and fuel consumption per tonkm : 0.154 [kg]
calculation *11* (operating cost)
fuel cost per hour at econ.speed (3211 [litre]):1926 [eur] (39 [pax-km/litre fuel])
fuel cost per seat 1000km flight (150 [pax] 2-class seating): 15.38 [eur/1000PK]
oil cost per hour: 3 [eur]
crew cost per hour : 900 [eur]
list price 2024 : 99 [mln USD]
average flying hours in 1 year : 2950 [hours] technical life : 22 [year]
real average service life : 22 [years]
depreciation : 22 [years] to 10% residual value
financing interest per flying hour : 759 [EUR]
write off per flying hour : 1273 [EUR]
mean time between engine failure (MTBF) : 18191 [hr]
insufficient engine reliability for ETOPS flights
can continue fly on 1 engine, low risk for emergency landing for PUF
Vueling Airbus A320-200 EC-MDZ c/n 6377 at the gate at Schiphol, pier C, 01 February 2025. It has IAE V2500 engines © bvdz
workhours per day : 11.04 [hr]
average flight hours till crash : 21.59 [mln hr] (7317 service years)
safe flight hours till fatality : 302321 [hr] (102.5 service years)
reservation pax liability/flying hour : 0.43 [SDR*] (0.53 [eur])
insurance cost per hour : 21 [eur] insurance rate : 0.2 [%]
engine maintenance cost per hour : 680.0 [eur]
wing maintenance cost per hour : 131.4 [eur]
fuselage maintenance cost per hour : 168.37 [eur]
tire life (time till worn out) : 84 [cycles]
maintenance cost per hour (excluding engines): 755 [eur]
direct operating cost per hour: 6318 [eur], DOC per km : 7.55 [eur]
DOC per seat 1000km flight (150 [pax] 2-class seating): 48.54 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 40.34 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 0.39 [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 : 3.32 [eur/pax]
airport landing fee / passenger : 3.32 [eur/pax]
retour ticket price 1000km trip : 168.51 [eur/pax]
price retour ticket Schiphol-Barcelona : 195.21 [eur/pax]
accidents with fatalities > see the accident file
Literature :
Airbus A320 family - Wikipedia
Jane´s all the world aircraft 1991-92 page 112
https://contentzone.eurocontrol.int/aircraftperformance/default.aspx?
https://www.airbus.com/en/airport-operations-and-technical-data/aircraft-characteristics
confidence rating regarding source data : medium - all information is only available from news, social media or unofficial sources
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 14 April 2025 contact : info.aircraftinvestigation@gmail.com ac jetpax 2020.py python 3.7.4
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