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weight and performance calculations for the Airbus A320-200 V2500
***** PRELIMINARY FILE ****
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
design :
production : 4752 aircraft
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 180 passengers
engine : 2 IAE V2500-A1 turbofan engines of 111.2 [KN] (24998.3 [lbf])
dimensions :
wingspan : 34.1 [m], length : 37.57 [m], height : 11.76 [m]
wing area : 122.4 [m^2] fuselage exterior width : 3.95 [m]
weights :
operating empty weight : 39980 [kg] max. structural payload : 20520 [kg]
Zero Fuel weight (ZFW) : 60500 [kg] max. landing weight (MLW) : 64500 [kg]
max.take-off weight : 73500 [kg] weight fuel : 19087 [kg] (23859 [liter])
performance :
Max. operating Mach number (Mmo) : 0.82 [Mach] (884 [km/hr]) at 10000 [m]
normal cruise speed : 870 [km/hr] (Mach 0.81 ) at 10000 [m] (29 [%] power)
economic cruise speed : 837 [km/hr] (Mach 0.78 ) at 10000 [m]
service ceiling : 11900 [m]
range with max fuel : 5600 [km] (ATA domestic fuel reserves - 370.0 [km] alternate)
description :
low-wing cantilever monoplane with retractable landing gear with nose wheel
two main 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
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
fuselage shape : 0 construction : all-metal aluminium-alloy stressed-skin construction with pressurized fuselage
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: 3.61 [m]
wing aspect ratio : 9.50 []
seize (span*length*height) : 15066 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 6.7 [kg/hr]
fuel consumption (econ. cruise speed) : 2676.0 [kg/hr] (3345.1 [litre/hr]) at 22 [%] power
distance flown for 1 kg fuel : 0.31 [km/kg] at 10000 [m] height, sfc : 55.4 [kg/KN/h]
total fuel capacity : 23859 [litre] (19087 [kg])
British Caledonian A320-231 G-BVYC
calculation : *3* (weight)
weight engine(s) dry : 4808.0 [kg] = 21.62 [kg/KN]
weight 68 litre oil tank : 5.80 [kg]
oil tank filled with 1.4 litre oil : 1.3 [kg]
oil in engine 2.7 litre oil : 2.4 [kg]
fuel in engine 12.1 litre fuel : 8.90 [kg]
weight fuel lines 47.9 [kg]
weight engine cowling 578.2 [kg]
weight thrust reversers 89.0 [kg]
total weight propulsion system : 5542 [kg](7.5 [%])
***************************************************************
Accommodation cabin facilities:
Inside Egyptair A320 SU-GBF
typical 2-class cabin layout for 150 passengers : economy : pitch : 81.3 [cm] 32.0 [-in]
( 3+3 ) seating in 25.4 rows
weight seats : 785.0 [kg]
high density seating passengers : 176 [pax] at 6 -abreast seating in 29.3 rows,
pitch 73.7 [cm] 29.0 [-in]
pax density, normal seating : 0.65 [m2/pax], high density seating : 0.56 [m2/pax]
weight 3 lavatories : 51.4 [kg]
weight 2 galleys : 122.0 [kg]
weight overhead stowage for hand luggage : 52.5 [kg]
weight 3 wardrobe closets : 30.0 [kg]
weight 53 windows : 47.5 [kg]
weight 4 1.83x0.86 [m] entrance/exit doors : 178.6 [kg]
weight 2 (130x122 cm) freight doors (belly) : 90.0 [kg]
belly baggage/cargo hold volume front : 18.25 [m3]
belly baggage/cargo hold volume rear : 23.70 [m3]
passenger compartment volume : 139 [m3]
passenger cabin max.width : 3.70 [m] cabin length : 27.51 [m] cabin height : 2.18 [m]
floor area : 97.7 [m2]
weight cabin facilities : 1356.9 [kg]
safety facilities:
weight 4 over wing emergency exits (91x51 cm): 85.1 [kg]
weight 8 hand fire extinguisher : 23 [kg]
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators : 97.5 [kg]
weight emergency flare installation : 10 [kg]
weight 4 emergency evacuation slides : 134.7 [kg]
weight safety equipment & facilities : 370 [kg]
fuselage construction:
fuselage aluminium frame : 10039 [kg]
floor loading (payload/m2): 210 [kg/m2]
weight rear pressure bulkhead : 154.2 [kg]
fuselage covering ( 353.9 [m2] duraluminium 2.41 [mm]) : 2248.1 [kg]
weight floor beams : 615.8 [kg]
weight cabin furbishing : 882.7 [kg]
weight cabin floor : 1257.7 [kg]
fuselage (sound proof) isolation : 256.3 [kg]
weight 8250 [litre] main central fuel tanks empty : 462.0 [kg]
weight empty 184 [litre] potable water tank : 16.3 [kg]
weight empty waste tank : 15.0 [kg]
weight fuselage structure : 15947.2 [kg]
Vueling A320-214 EC-HHA cockpit
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 EFIS (CRT PFD+ND) : 8 [kg]
weight engine monitoring system ECAM : 6 [kg]
weight avionics : 81.0 [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 : 333 [m3]
weight air-conditioning and pressurisation system : 184 [kg]
weight APU / engine starter: 55.6 [kg]
weight lighting : 49.5 [kg]
weight engine-driven 40kVA electricity generators : 37.5 [kg]
weight controls (sidestick FBW): 10.7 [kg]
weight systems : 337.0 [kg]
total weight fuselage : 18092 [kg](24.6 [%])
***************************************************************
total weight aluminium ribs (1046 ribs) : 2621 [kg]
weight engine mounts : 111 [kg]
weight 6 fuel tanks empty for total 15609 [litre] fuel : 874 [kg]
weight wing covering (painted aluminium 4.06 [mm]) : 2685 [kg]
total weight aluminium spars (multi-cellular wing structure) : 2316 [kg]
weight wings : 7621 [kg]
weight wing/square meter : 62.27 [kg]
weight thermal leading-edge anti-icing : 37.5 [kg]
weight ailerons (3.7 [m2]) : 114.4 [kg]
weight fin (13.9 [m2]) : 651.3 [kg]
weight rudder (10.4 [m2]) : 311.1 [kg]
weight tailplane (stabilizer) (31.8 [m2]): 1390.4 [kg]
weight elevators (10.7 [m2]): 179.7 [kg]
weight flight control hydraulic servo actuators: 43.4 [kg]
weight trailing-edge double slotted flaps (21.3 [m2]) : 568.7 [kg]
weight leading edge slats (6.6 [m2]) : 117.1 [kg]
weight spoilers (3.5 [m2]) : 58.9 [kg]
total weight wing surfaces & bracing : 12079 [kg] (16.4 [%])
*******************************************************************
tyre pressure main wheels : 11.80 [Bar] (nitrogen), ply rating : 23 PR
tyre speed limit : 364 [km/hr]
Aircraft Classification Number, MTOW on rigid runway and medium subgrade strength :
47 [ ]
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
Can only operate from paved runways
wheel pressure : 16170.0 [kg]
weight 4 Dunlop main wheels (1240 [mm] by 455 [mm]) : 631.2 [kg]
weight 2 nose wheels : 157.8 [kg]
weight multi-disc wheel-brakes : 60.5 [kg]
weight flywheel detector type anti-skid units : 5.4 [kg]
weight oleo-pneumatic shock absorbers : 80.7 [kg]
weight wheel hydraulic operated retraction system : 611.5 [kg]
weight undercarriage struts with axle 1479.7 [kg]
total weight landing gear : 3026.8 [kg] (4.1 [%]
*******************************************************************
********************************************************************
calculated empty weight : 38740 [kg](52.7 [%])
weight oil for 7.7 hours flying : 57.1 [kg]
weight lifejackets : 67.5 [kg]
weight 3 life rafts : 93.8 [kg]
weight catering : 203.3 [kg]
weight water : 162.6 [kg]
weight crew : 567 [kg]
weight crew lugage,nav.chards,flight doc.,miscell.items : 89 [kg]
operational weight empty : 39980 [kg] (54.4 [%])
********************************************************************
weight 150 passengers : 11550 [kg]
weight luggage : 2400 [kg]
weight cargo : 6570 [kg] (cargo+luggage/m3 belly : 200 [kg/m3])
zero fuel weight (ZFW): 60500 [kg](82.3 [%])
weight fuel for landing (1.5 hours flying) : 4000 [kg]
max. landing weight (MLW): 64500 [kg](87.8 [%])
max. fuel weight : 59067 [kg] (80.4 [%])
payload with max fuel : 155 passengers+luggage 14433 [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 : 6.3 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 1.2 [g]
design flight time : 2.71 [hours]
design cycles : 27954 sorties, design hours : 75766 [hours]
max. wing loading (MTOW & flaps retracted) : 600 [kg/m2]
wing stress (2 g) during operation : 177 [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) : 13.63 ["]
max. angle of attack (full flaps) : 17.83 ["]
angle of attack at max. speed : 3.31 ["]
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 : 1.36 [ ]
max. lift coefficient full flaps : 2.39 [ ]
drag coefficient at max. speed : 0.0348 [ ]
drag coefficient at econ. cruise speed : 0.0354 [ ]
induced drag coefficient at econ. cruise speed : 0.0094 [ ]
drag coefficient (zero lift) : 0.0260 [ ]
lift/drag ratio at max. speed : 12.78 [ ]
calculation : *8* (speeds
take-off safety speed (V2) : 266 [km/u]
take-off (initial climb) speed (Vto) : 316 [km/u]
stalling speed clean at sea-level (OW loaded : 70824 [kg]): 297 [km/u]
max. rate of climb speed : 586 [km/hr] at sea-level
max. endurance speed (Vbe): 605 [km/u] min. fuel/hr : 2366 [kg/hr] at height : 8839 [m]
max. range speed (Vbr): 884 [km/u] min. fuel consumption : 2.958 [kg/km] at cruise height : 11278 [m]
cruising speed : 870 [km/hr] at 10000 [m] (power:23 [%])
max. operational speed (Mmo) : 884.00 [km/hr] (Mach 0.82 ) at 10000 [m] (power:23.0 [%])
airflow at cruise speed per engine : 203.1 [kg/s]
Adria Airbus A320-231 at Schiphol © bvdz
speed of thrust jet : 1315 [km/hr]
initial descent speed 10000 - 7315 [m]: Mach 0.75
descent speed 7315 - 3048 [m]: 537 [km/u]
approach speed 3048 - 500 [m] (clean): 463 [km/u]
stalling speed clean at 500 [m] height at Max.Landing Weight : 64500 [kg]): 290 [km/u]
final approach speed at sea-level with full flaps (normal landing weight) (Vapp): 251 [km/u]
ICAO Aircraft Approach Category (APC) : C
landing speed at sea-level (normal landing weight(Vtd): 64317 [kg]): 222 [km/hr]
stalling speed at sea-level with full flaps (normal landing weight): 193 [km/u]
rate of climb at sea-level ROC (loaded) : 1194 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF / MTOW) : 635 [m/min]
rate of descent: 457 [m/min]
Cyprus Airways A320-231 5B-DBC “Tefkros”
calculation : *9* (regarding various performances)
high wheel pressure, can only take off from paved runways
take-off distance at sea-level concrete runway : 2360 [m]
ICAO Aerodrome Reference Code : 3C
take-off distance at sea-level over 15 [m] height : 2483 [m]
landing run : 1039 [m]
landing run (C.A.R.) from 15 [m] at SL, dry runway : 1547 [m]
landing run (C.A.R.) from 15 [m] at SL, wet runway : 1847 [m]
lift/drag ratio : 14.68 [ ]
climb to 5000 [m] with max payload : 3.88 [min]
climb to 10000 [m] with max payload : 11.93 [min]
descent time from 10000 [m] to 250 [m] : 24.33 [min]
ceiling limited by max. pressure differential 12250 [m]
theoretical ceiling fully loaded (mtow- 60 min.fuel: 70824 [kg] ) : 15500 [m]
calculation *10* (action radius & endurance)
range with max. payload: 3963 [km] with 20520.0 [kg] max. useful load (68.1 [%] fuel)
range with high density pax: 5328 [km] with 176 passengers (90.0 [%] fuel)
range with typical two-class pax: 5994 [km] with 150 passengers (100.0 [%] fuel)
range with max.fuel : 5970 [km] with 7 crew and 155 passengers and 100.0 [%] fuel
ferry range : 6720 [km] with 2 crew and zero payload (100.0 [%] fuel)
max range theoretically with additional fuel tanks total 42863.6 [litre] fuel : 11405 [km]
Available Seat Kilometres (ASK) : 899103 [paskm]
useful load with range 1000km : 20520 [kg]
useful load with range 1000km : 176 passengers
production (theor.max load): 17852 [tonkm/hour]
production (useful load): 17852 [tonkm/hour]
production (passengers): 130500 [paskm/hour]
oil and fuel consumption per tonkm : 0.150 [kg]
fuel cost per paskm : 0.021 [eur]
crew cost per paskm : 0.007 [eur]
Indigo A320-232 VT-IES c/n 5090 at Dubai apt. (DXB), January 2013. Indigo has a fleet of 267 A320’s
list price : 79 [mln USD]
economic hours : 65000 [hours] is 14 [%] less then design hours
time between engine failure : 835 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
writing off per paskm : 0.008 [eur]
insurance per paskm : 0.0024 [eur]
maintenance cost per paskm : 0.013 [eur]
direct operating cost per paskm : 0.051 [eur]
direct operating cost per tonkm (max. load): 0.372 [eur]
direct operating cost per tonkm (normal useful load): 0.372 [eur]
accidents with fatalities > see the accident file
Literature :
wikipedia
Jane´s all the world aircraft 1990
https://contentzone.eurocontrol.int/aircraftperformance/default.aspx?
https://www.airbus.com/en/airport-operations-and-technical-data/aircraft-characteristics
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