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weight and performance calculations for the Sud Aviation SE-210 Caravelle VIN
***** PRELIMINARY FILE ****
Note the stairs – entrance at the tail
Sud Aviation SE-210 Caravelle VIN
role : jet airliner
importance : ****
first flight : 10 September 1960 operational : January 1961 (SABENA)
country : France
design :
production : 53 VIN aircraft (total 282 Caravelles were built)
general information :
Version with more powerful engines and improved air-conditioning.
The VIN had a higher MTOW, it had a longer range and was faster.
Lift/drag ratio (L/D) max. 18.4. In glide flight the speed is 265 km/h, the descending
speed is then 4 m/s. Max. descent speed : 33 [m/s].
Cabin width at floor : 2.69 [m], cabin max.width : 3.00 [m]
primary users : Sabena(8), Alitalia(10), Saeta, Corse Air, Minerve, Europe A.S., Pushpaka
aviation, Yugoslav airlines, Air Algerie(2), Aerolineas Argentinas, Transavia (PH-TVV
& PH-TVW)
accommodations:
flight crew : 3 cabin crew : 3
flight crew consist of pilot, co-pilot and flight engineer
passengers : seating for 86 in two class : 10 business class and 76 economy class seats ( 32 -in pitch)
high density seating for 94-99 passengers
engine : 2 Rolls Royce Avon RA.2 Mk.531 turbojet engines of 54.28 [KN](12202.4 [lbf])
dimensions :
wingspan : 34.3 [m], length : 32.01 [m], height : 8.72 [m]
wing area : 146.7 [m^2]
weights :
operating empty weight : 28830 [kg] max. structural payload : 8170 [kg]
Zero Fuel weight (ZFW) : 37000 [kg] max. landing weight (MLW) : 45700 [kg]
max.take-off weight : 48000 [kg] weight fuel : 15200 [kg] (19000 [liter])
performance :
Max. operating Mach number (Mmo) : 0.75 [Mach] (838 [km/hr]) at 7620 [m]
normal cruise speed : 790 [km/hr] (Mach 0.72 ) at 9000 [m] (39 [%] power)
service ceiling : 9150 [m]
range with max fuel : 2628 [km] and allowance for 245.1 [km] diversion and 30 [min] hold
VT-DVI Caravelle VIN flying with Pushpaka Aviation , India
description :
low-wing cantilever monoplane with retractable landing gear with nose wheel
tapered multi-cellular wing with flush-riveted stressed skin
with Fowler flaps air foil : unknown
sweep angle 3/4 chord: 20.0 [°]
engines attached to the tail, landing gear attached to the wings, fuel tanks in the wings
construction : all-metal aluminium-alloy stressed-skin construction with pressurized fuselage
fuselage shape : O
calculation : *1* (dimensions)
measured wing chord : 4.28 [m] at 50% wingspan
mean wing chord : 4.28 [m]
calculated average wing chord tapered wing with rounded tips: 4.20 [m]
wing aspect ratio : 8.02 []
seize (span*length*height) : 9574 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 54.3 [kg/hr]
fuel consumption (econ. cruise speed) : 4026.3 [kg/hr] (5032.9 [litre/hr]) at 39 [%] power
distance flown for 1 kg fuel : 0.20 [km/kg] at 9000 [m] height, sfc : 95.0 [kg/KN/h]
total fuel capacity : 19000 [litre] (15200 [kg])
calculation : *3* (weight)
weight engine(s) dry : 2660.0 [kg] = 24.50 [kg/KN]
weight 243.6 litre oil tank : 20.71 [kg]
oil tank filled with 0.7 litre oil : 0.6 [kg]
oil in engine 18.1 litre oil : 16.3 [kg]
fuel in engine 13.3 litre fuel : 9.77 [kg]
weight fuel lines 19.0 [kg]
weight engine cowling 325.7 [kg]
total weight propulsion system : 3052 [kg](6.4 [%])
***************************************************************
fuselage aluminium frame : 7595 [kg]
typical cabin layout for 86 passengers : economy : pitch : 81 [cm] ( 3+2 ) seating in 17.7 rows
Minerve Caravelle VIN F-GATZ
pax density (normal seating) : 0.69 [m2/pax]
high density seating passengers : 96 at 5 -abreast seating in 19.2 rows, pitch 76 [cm]
weight 1 toilets : 20.2 [kg]
weight 4 hand fire extinguisher : 13 [kg]
weight 1 galleys : 45.8 [kg]
weight overhead stowage for hand luggage : 30.1 [kg]
weight 2 closets : 8.6 [kg]
weight 37 windows : 33.7 [kg]
weight 4 over wing emergency exits : 60 [kg]
weight oxygen masks & oxygen generators : 55.9 [kg]
weight emergency flare installation : 10 [kg]
weight 2 emergency evacuation slides : 20.3 [kg]
weight tail stair : 70.0 [kg]
weight 3 entrance/exit doors : 48.0 [kg]
weight 2 freight doors (belly) : 8.0 [kg]
weight ladies’ powder room : 16 [kg]
weight men’s dressing room : 12 [kg]
weight diplomatic mail locker : 2 [kg]
cabin volume (usable), excluding flight deck : 108.02 [m3]
passenger cabin max.width : 3.00 [m] cabin length : 21.89 [m] cabin height : 2.00 [m]
VIN F-BVPZ, 2+3 seat arrangement
floor area : 59.2 [m2]
pressure difference :0.58 [kg/cm2]
weight rear pressure bulkhead : 127.2 [kg]
weight air pressurization system : 32.8 [kg]
fuselage covering ( 224.7 [m2] duraluminium 3.03 [mm]) : 1785.4 [kg]
weight floor beams : 205.6 [kg]
weight cabin furbishing : 335.4 [kg]
weight cabin floor : 671.4 [kg]
fuselage (sound proof) isolation : 189.2 [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: 27.1 [kg]
weight lighting : 21.5 [kg]
weight electricity generator : 21.5 [kg]
weight controls : 13.9 [kg]
weight seats : 460.0 [kg]
weight air conditioning : 129 [kg]
weight engine mounts : 54 [kg]
total weight fuselage : 11908 [kg](24.8 [%])
***************************************************************
total weight aluminium ribs (573 ribs) : 1712 [kg]
weight fuel tanks empty for total 19000 [litre] fuel : 1064 [kg]
SABENA was the launch customer for the VIN
weight wing covering (painted aluminium 3.08 [mm]) : 2440 [kg]
total weight aluminium spars (multi-cellular wing structure) : 2859 [kg]
weight wings : 7011 [kg]
weight wing/square meter : 47.79 [kg]
weight rubber de-icing boots : 37.7 [kg]
weight fin & rudder (13.7 [m2]) : 654.7 [kg]
weight stabilizer & elevator (16.5 [m2]): 789.9 [kg]
weight flight control hydraulic servo actuators: 43.6 [kg]
weight fowler flaps (10.2 [m2]) : 249.4 [kg]
total weight wing surfaces & bracing : 9851 [kg] (20.5 [%])
*******************************************************************
wheel pressure : 5280.0 [kg]
weight 8 Dunlop main wheels (1130 [mm] by 174 [mm]) : 1475.3 [kg]
weight 2 Dunlop nose wheels : 184.4 [kg]
weight hydraulic wheel-brakes : 37.0 [kg]
weight pneumatic-hydraulic shock absorbers : 49.3 [kg]
weight wheel hydraulic operated retraction system : 632.3 [kg]
weight undercarriage struts with axle 751.7 [kg]
total weight landing gear : 3130.1 [kg] (6.5 [%]
*******************************************************************
********************************************************************
calculated empty weight : 27941 [kg](58.2 [%])
weight oil for 4.0 hours flying : 216.7 [kg]
weight catering : 114.4 [kg]
weight water : 45.8 [kg]
weight crew : 486 [kg]
weight crew lugage,nav.chards,flight doc.,miscell.items : 26 [kg]
operational weight empty : 28830 [kg] (60.1 [%])
********************************************************************
F-BYAT flying with Corse-Air.
weight 86 passengers : 6622 [kg]
weight luggage : 1376 [kg]
weight cargo : 172 [kg]
zero fuel weight (ZFW): 37000 [kg](77.1 [%])
weight fuel for landing (2.2 hours flying) : 8700 [kg]
max. landing weight (MLW): 45700 [kg](95.2 [%])
max. fuel weight : 44030 [kg] (91.7 [%])
payload with max fuel : 43 passengers+luggage 3970 [kg]
published maximum take-off weight : 48000 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 442 [kg/KN]
power loading (operational without useful load) : 432 [kg/kN]
power loading (Take-off) 1 PUF: 884 [kg/KN]
high power loading if engine failure, can not stay airborne
max. total take-off power : 108.6 [KN]
calculation : *5* (loads)
manoeuvre load : 7.0 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 1.8 [g]
design flight time : 2.66 [hours]
design cycles : 11106 sorties, design hours : 29556 [hours]
operational wing loading : 3129 [N/m^2]
wing stress (3 g) during operation : 196 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.16 ["]
max. angle of attack (stalling angle, clean) : 12.16 ["]
angle of attack at max. speed : 1.28 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.10 [ ]
lift coefficient at max. speed : 0.21 [ ]
lift coefficient at max. angle of attack : 1.15 [ ]
max. lift coefficient full flaps : 1.42 [ ]
induced drag coefficient at max.speed : 0.0023 [ ]
drag coefficient at max. speed : 0.0219 [ ]
drag coefficient (zero lift) : 0.0196 [ ]
lift/drag ratio at max. speed : 9.63 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 43974 [kg]): 233 [km/u]
stalling speed at sea-level with full flaps (normal landing weight): 213 [km/u]
landing speed at sea-level (normal landing weight : 45620 [kg]): 245 [km/hr]
max. rate of climb speed : 530 [km/hr] at sea-level
max. endurance speed : 440 [km/u] min. fuel/hr : 2400 [kg/hr] at height : 7010 [m]
max. range speed : 600 [km/u] min. fuel consumption : 4.620 [kg/km] at cruise height : 7620 [m]
cruising speed : 790 [km/hr] at 9000 [m] (power:34 [%])
max. operational speed (Mmo) : 838.00 [km/hr] (Mach 0.75 ) at 7620 [m] (power:43.9 [%])
airflow : 132.2 [kg/s]
speed of thrust jet : 1943 [km/hr]
climbing speed at sea-level (loaded) : 1246 [m/min]
climbing speed at 1000 [m] with 1 engine out (PUF / MTOW) : 1189 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 292.0 [km/u]
high wheel pressure, can only take off from paved runways
take-off distance at sea-level concrete runway : 1437 [m]
take-off distance at sea-level over 15 [m] height : 1543 [m]
landing run : 1196 [m]
landing run from 15 [m] : 2063 [m]
lift/drag ratio : 15.69 [ ]
max. theoretical ceiling : 18100 [m] with flying weight :43974 [kg] line 3359
climb to 1000m with max payload : 0.79 [min]
climb to 2000m with max payload : 1.53 [min]
climb to 3000m with max payload : 2.24 [min]
climb to 5000 [m] with max payload : 3.52 [min]
minimum flying speed at 9150 [m] : 438 [km/hr]
theoretical ceiling fully loaded (mtow- 60 min. fuel:43974 [kg] ) : 18100 [m]
calculation *10* (action radius & endurance)
published range : 2628 [km] with 6 crew and 5776 [kg] useful load and 88.1 [%] fuel
range : 2158 [km] with 8170.0 [kg] max. useful load (72.4 [%] fuel)
range : 2192 [km] with 86.0 passengers with each 16 [kg] luggage and 73.5 [%] fuel
range max. fuel : 2982 [km] with 3970.0 [kg] useful load and 100.0 [%] fuel
Available Seat Kilometres (ASK) : 188515 [paskm]
max range theoretically with additional fuel tanks total 23962.5 [litre] fuel : 4149 [km]
useful load with range 500km : 16622 [kg]
HC-BAE van Saeta, Ecuador
useful load with range 500km : 86 passengers
production (theor.max load): 13131 [tonkm/hour]
production (useful load): 6454 [tonkm/hour]
production (passengers): 67940 [paskm/hour]
combi aircraft mail/freight/passengers
oil and fuel consumption per tonkm : 0.311 [kg]
fuel cost per paskm : 0.060 [eur]
crew cost per paskm : 0.011 [eur]
economic hours : 22300 [hours] is less then design hours
time between engine failure : 962 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
writing off per paskm : 0.015 [eur]
insurance per paskm : 0.0014 [eur]
maintenance cost per paskm : 0.013 [eur]
direct operating cost per paskm : 0.101 [eur]
direct operating cost per tonkm (max. load): 0.521 [eur]
direct operating cost per tonkm (normal useful load): 1.060 [eur]
Literature
Praktisch handboek vliegtuigen deel 5 page 203
Jane’s all the world aircraft 1964-1965 page 59
Alles over straalverkeersvliegtuigen page 134
Air International oct’97 page 252
Verkehrsflugzeuge page 102
Verkeersvliegtuigen Moussault page
wikipedia
Sud Aviation Caravelle (michaelprophet.com)
F-BYCA of Europe A.S.
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