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weight and performance calculations for the Sud Aviation SE-210 Super Caravelle 10B
***** PRELIMINARY FILE ****
Sud Aviation SE-210 Super Caravelle 10B
importance : ***
first flight : 3 March 1964 operational : 16 August 1964 (Finnair)
country : France
design :
production : 22 aircraft
general information :
The VIR was followed by the 10A with GE CJ805-23C turbofans of 7300 kg of thrust. These were so-called aft fans. It made its first flight on Dec. 28 , 1960 . This version did not go into production. The 10B with P&W JT8D-1 turbofans did go into production. It was first referred to as Super B, later as Super Caravelle.
Equipped with 2 doors and 1 exit in the tail as well as 4 emergency exits.
primary users : Finnair, Sterling Airways, Syrian Arab Airlines
Accommodation:
flight crew : 3 cabin crew : 3
flight crew consist of pilot, co-pilot and flight engineer
passengers : seating for 99 in two class : 12 business class and 87 economy class seats
( 32 -in pitch)
high density seating for 104 passengers
engine : 2 Pratt & Whitney JT8D-1 turbofan engines of 62.27 [KN](13998.6 [lbf])
dimensions :
wingspan : 34.3 [m], length : 33.01 [m], height : 8.72 [m]
wing area : 146.7 [m^2]
weights :
empty weight : 27623021 [kg]
operating empty weight : 30235 [kg] max. structural payload : 9265 [kg]
Zero Fuel weight (ZFW) : 39500 [kg] max. landing weight (MLW) : 49500 [kg]
max.take-off weight : 52000 [kg] weight fuel : 17600 [kg] (22000 [liter])
performance :
Max. operating Mach number (Mmo) : 0.75 [Mach] (835 [km/hr]) at 7620 [m]
normal cruise speed : 800 [km/hr] (Mach 0.74 ) at 10000 [m] (37 [%] power)
service ceiling : 10700 [m]
range with max fuel : 3296 [km] and allowance for 333.8 [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 : unknown
sweep angle 3/4 chord: 20.0 [°]
engines attached to the tail, landing gear attached to the wings, fueltanks 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) : 9873 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 12.5 [kg/hr]
fuel consumption (econ. cruise speed) : 3763.4 [kg/hr] (4704.3 [litre/hr]) at 37 [%] power
distance flown for 1 kg fuel : 0.21 [km/kg] at 10000 [m] height, sfc : 82.0 [kg/KN/h]
total fuel capacity : 22000 [litre] (17600 [kg])
calculation : *3* (weight)
weight engine(s) dry : 2908.0 [kg] = 23.35 [kg/KN]
weight 71.2 litre oil tank : 6.05 [kg]
oil tank filled with 0.8 litre oil : 0.7 [kg]
oil in engine 20.8 litre oil : 18.7 [kg]
fuel in engine 15.3 litre fuel : 11.21 [kg]
weight fuel lines 22.0 [kg]
weight engine cowling 373.6 [kg]
total weight propulsion system : 3340 [kg](6.4 [%])
***************************************************************
fuselage aluminium frame : 7766 [kg]
typical cabin layout for 99 passengers : economy : pitch : 81 [cm] ( 3+2 ) seating in 20.4 rows
pax density (normal seating) : 0.62 [m2/pax]
high density seating passengers : 110 at 5 -abreast seating in 22.1 rows, pitch 76 [cm]
weight 2 toilets : 25.9 [kg]
weight 5 hand fire extinguisher : 15 [kg]
weight lifejackets : 45.0 [kg]
weight 1 galleys : 65.3 [kg]
weight overhead stowage for hand luggage : 34.6 [kg]
weight 2 closets : 9.9 [kg]
weight 43 windows : 38.5 [kg]
weight 4 overwing emergency exits : 100.1 [kg]
weight oxygen masks & oxygen generators : 64.4 [kg]
weight tail entrance stairs : 78.8 [kg]
weight emergency flare installation : 10 [kg]
UTA flew with the Caravelle 10B1R variant
weight 2 emergency evacuation slides : 26.0 [kg]
weight 3 entrance/exit doors : 175.1 [kg]
weight 2 freight doors (belly) : 83.4 [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 : 112.81 [m3]
passenger cabin max.width : 3.00 [m] cabin length : 22.86 [m] cabin height : 2.00 [m]
floor area : 61.8 [m2]
pressure difference :0.58 [kg/cm2]
weight rear pressure bulkhead : 125.6 [kg]
weight air pressurization system : 34.3 [kg]
fuselage covering ( 232.8 [m2] duraluminium 2.99 [mm]) : 1820.9 [kg]
weight floor beams : 212.3 [kg]
weight cabin furbishing : 388.5 [kg]
weight cabin floor : 781.8 [kg]
fuselage (sound proof) isolation : 167.6 [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: 31.1 [kg]
weight lighting : 24.8 [kg]
weight electricity generator : 24.8 [kg]
weight controls : 14.1 [kg]
weight seats : 525.0 [kg]
weight air conditioning : 148 [kg]
weight engine mounts : 62 [kg]
total weight fuselage : 12833 [kg](24.7 [%])
***************************************************************
total weight aluminium ribs (621 ribs) : 1854 [kg]
weight fuel tanks empty for total 22000 [litre] fuel : 1232 [kg]
weight wing covering (painted aluminium 3.07 [mm]) : 2429 [kg]
total weight aluminium spars (multi-cellular wing structure) : 2798 [kg]
weight wings : 7082 [kg]
weight wing/square meter : 48.27 [kg]
weight rubber de-icing boots : 37.7 [kg]
weight fin & rudder (13.7 [m2]) : 661.2 [kg]
weight stabilizer & elevator (16.5 [m2]): 797.8 [kg]
weight flight control hydraulic servo actuators: 44.1 [kg]
weight fowler flaps (10.2 [m2]) : 251.9 [kg]
total weight wing surfaces & bracing : 10106 [kg] (19.4 [%])
*******************************************************************
wheel pressure : 5720.0 [kg]
weight 8 Dunlop main wheels (1130 [mm] by 174 [mm]) : 1546.6 [kg]
weight 2 Dunlop nose wheels : 193.3 [kg]
weight hydraulic wheel-brakes : 39.5 [kg]
weight pneumatic-hydraulic shock absorbers : 52.7 [kg]
weight wheel hydraulic operated retraction system : 638.1 [kg]
weight undercarriage struts with axle 688.3 [kg]
total weight landing gear : 3158.4 [kg] (6.1 [%]
*******************************************************************
********************************************************************
calculated empty weight : 29438 [kg](56.6 [%])
weight oil for 4.9 hours flying : 61.6 [kg]
weight catering : 163.2 [kg]
weight water : 65.3 [kg]
weight crew : 486 [kg]
weight crew lugage,nav.chards,flight doc.,miscell.items : 21 [kg]
operational weight empty : 30235 [kg] (58.1 [%])
********************************************************************
weight 99 passengers : 7623 [kg]
Interior F-GHMU Caravelle 10B3 air Toulouse
weight luggage : 1584 [kg]
weight cargo : 58 [kg]
zero fuel weight (ZFW): 39500 [kg](76.0 [%])
weight fuel for landing (2.7 hours flying) : 10000 [kg]
max. landing weight (MLW): 49500 [kg](95.2 [%])
max. fuel weight : 47835 [kg] (92.0 [%])
payload with max fuel : 45 passengers+luggage 4165 [kg]
published maximum take-off weight : 52000 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 418 [kg/KN]
power loading (operational without useful load) : 407 [kg/kN]
power loading (Take-off) 1 PUF: 835 [kg/KN]
high powerloading if engine failure, can not stay airborne
max. total take-off power : 124.5 [KN]
calculation : *5* (loads)
manoeuvre load : 6.4 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 1.6 [g]
design flight time : 3.30 [hours]
design cycles : 8890 sorties, design hours : 29302 [hours]
operational wing loading : 3389 [N/m^2]
wing stress (3 g) during operation : 211 [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 : 1.51 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.10 [ ]
lift coefficient at max. speed : 0.23 [ ]
lift coefficient at max. angle of attack : 1.15 [ ]
max. lift coefficient full flaps : 1.42 [ ]
induced drag coefficient at max.speed : 0.0027 [ ]
drag coefficient at max. speed : 0.0231 [ ]
drag coefficient (zero lift) : 0.0203 [ ]
lift/drag ratio at max. speed : 9.95 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 48237 [kg]): 244 [km/u]
stalling speed at sea-level with full flaps (normal landing weight): 222 [km/u]
V : 336.54 te laag, Cl > Clmax berekening PR nodig klopt niet meer cl : 1.87 line 216
flying weight (fw) : 50692.0
landing speed at sea-level (normal landing weight : 49386 [kg]): 255 [km/hr]
max. rate of climb speed : 555 [km/hr] at sea-level
max. endurance speed : 337 [km/u] min. fuel/hr : 2258 [kg/hr] at height : 1524 [m]
max. range speed : 660 [km/u] min. fuel consumption : 3.951 [kg/km] at cruise height : 8839 [m]
cruising speed : 800 [km/hr] at 10000 [m] (power:30 [%])
max. operational speed (Mmo) : 835.00 [km/hr] (Mach 0.75 ) at 7620 [m] (power:40.1 [%])
airflow : 149.9 [kg/s]
speed of thrust jet : 1902 [km/hr]
climbing speed at sea-level (loaded) : 1395 [m/min]
climbing speed at 1000 [m] with 1 engine out (PUF / MTOW) : 1333 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 303.9 [km/u]
high wheel pressure, can only take off from paved runways
take-off distance at sea-level concrete runway : 1464 [m]
take-off distance at sea-level over 15 [m] height : 1563 [m]
landing run : 1293 [m]
landing run from 15 [m] : 2195 [m]
lift/drag ratio : 15.38 [ ]
max. theoretical ceiling : 17600 [m] with flying weight :48237 [kg] line 3359
climb to 1000m with max payload : 0.70 [min]
climb to 2000m with max payload : 1.37 [min]
climb to 3000m with max payload : 2.00 [min]
climb to 5000 [m] with max payload : 3.14 [min]
minimum flying speed at 10700 [m] : 505 [km/hr]
theoretical ceiling fully loaded (mtow- 60 min. fuel:48237 [kg] ) : 17600 [m]
calculation *10* (action radius & endurance)
published range : 3296 [km] with 6 crew and 6260 [kg] useful load and 88.1 [%] fuel
range : 2657 [km] with 9265.0 [kg] max. useful load (71.0 [%] fuel)
range : 2670 [km] with 99.0 passengers with each 16 [kg] luggage and 71.4 [%] fuel
range max. fuel : 3741 [km] with 4165.0 [kg] useful load and 100.0 [%] fuel
Available Seat Kilometres (ASK) : 264281 [paskm]
max range theoretically with additional fuel tanks total 27206.2 [litre] fuel : 5509 [km]
useful load with range 500km : 19413 [kg]
useful load with range 500km : 99 passengers
production (theor.max load): 15530 [tonkm/hour]
production (useful load): 7412 [tonkm/hour]
production (passengers): 79200 [paskm/hour]
combi aircraft mail/freight/passengers
oil and fuel consumption per tonkm : 0.243 [kg]
fuel cost per paskm : 0.048 [eur]
crew cost per paskm : 0.009 [eur]
Air Toulouse 10B3 cockpit F-GHMU
economic hours : 22300 [hours] is less then design hours
time between engine failure : 1020 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
writing off per paskm : 0.014 [eur]
insurance per paskm : 0.0010 [eur]
maintenance cost per paskm : 0.013 [eur]
direct operating cost per paskm : 0.085 [eur]
direct operating cost per tonkm (max. load): 0.435 [eur]
direct operating cost per tonkm (normal useful load): 0.912 [eur]
Literature :
Jane’s all the world aircraft 1964-1965 page 60
Verkeersvliegtuigen page 9
Verkehrsflugzeuge page 105
Jane’s commercial transport aircraft page 17
Praktisch handboek vliegtuigen deel 5 page 203
Sud Aviation Caravelle - Wikipedia
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/
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(c) B van der Zalm 27 June 2022 contact : info.aircraftinvestigation@gmail.com python 3.7.4