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weight and performance calculations for the Sud Aviation SE-210 Caravelle 10R
Iberia Caravelle 10R EC-BIE c/n 230 at Geneva, September 1967 .
Sud Aviation SE-210 Caravelle 10R
role : short-range regional jet airliner
importance : ***
first flight : 18 January 1965 operational : Augus 1965 (Alia)
country : France
ICAO aircraft type designator : S210
production : 20 aircraft
general information :
The 10R, also referred to as 10B1R, was a combination of the VI-R fuselage equipped with
the Caravelle 10B JT8D-7 turbofan engines, creating a smaller but higher powered aircraft.
Basic take-off weight was 52.000 but with a strengthened frame this could be raised to
54.000 kgs.
primary users : Alia, Iberia, LTU, SATA, Sterling, Transeuropa, UTA ,Aero Lloyd , CTA,
Hispania, SAT
Accommodation :
flight crew : 2 cabin crew : 3
passengers : seating for 76 in two class : 16 first class and 60 coach class seats ( 34 -in pitch)
high density seating for max 99 passengers (equal to exit limit)
engine : 2 Pratt & Whitney JT8D-7 turbofan engines of 62.27 [KN] (13999 [lbf])
dimensions :
wingspan : 34.3 [m], length overall: 32.01 [m], length of fuselage : 32.01 [m] height : 8.72
[m] wing area gross : 146.7 [m^2] fuselage exterior width : 3.2 [m]
weights :
manufacturer^s weight empty : 26725 [kg]
operating empty weight : 29075 [kg] max. structural payload : 9425 [kg]
Zero Fuel weight (ZFW) : 38500 [kg] max. landing weight (MLW) : 49500 [kg]
max. take-off weight : 52000 [kg] weight usable fuel : 14915 [kg] (19000 [litres])
performance :
Max. operating Mach number (Mmo) : 0.762 [Mach] (848 [km/hr]) at 7620 [m]
critical Mach speed : 0.75 [Mach]
max. cruising speed : 800 [km/hr] (Mach 0.751 ) at 10670 [m] (37 [%] power)
economic cruising speed : 750 [km/hr] (Mach 0.70 ) at 10670 [m]
service ceiling : 9150 [m]
range with max fuel and MTOW : 2900 [km] (ATA domestic fuel reserves - 370.0 [km]
alternate)
description :
*Cantilever low-wing monoplane with retractable landing gear with nose wheel
engines attached to the tail, landing gear attached to the wings, fuel tanks in the wings
*Wings : all-metal three-spar wing structure with trailing edge single-slotted Fowler flaps
with cambered leading edge without flaps ,with airbrakes and spoilers airfoil : NACA
average thickness/chord ratio : 12.0 [%], sweep angle 3/4 chord: 20.0 [°]
incidence at root : 2.00 [°], dihedral : 3.0 [°]
*Tail Unit: Cantilever all-metal structure with tailplane mounted at tip of fin
*Fuselage : Pressurized conventional all-metal semi-monocoque fail safe structure of circular
section
Alia- Royal Jordanian Caravelle 10B1R JY-ADG c/n 236 at London-Heathrow (LHR), April 1973.
calculation : *1* (dimensions) :
wing chord at root : 6.33 [m]
wing chord at tip : 2.23 [m]
measured geometric tail-angle : 11.0 [° ]
taper ratio : 0.352 [ ]
mean wing chord : 4.28 [m]
wing aspect ratio : 8.02 []
Oswald factor (e): 0.695 []
seize (span*length*height) : 9574 [m^3]
calculation : *2* (fuel consumption) :
oil consumption : 4.2 [kg/hr]
fuel consumption (econ. cruise speed) : 3420.9 [kg/hr] (4357.8 [litre/hr]) at 34 [%] power
fuel burn per seat per hour (average seating) : 49.80 [litre], sfc : 80.6 [kg/KN/h]
calculation : *3* (weight) :
weight engine(s) dry : 3000.0 [kg] = 24.09 [kg/KN]
weight 27.0 litre oil tank : 2.30 [kg]
oil tank filled with 0.8 litre oil : 0.7 [kg]
oil in engine 1.5 litre oil : 1.4 [kg]
weight all fuel lines and pumps containing 72 litres fuel : 39.1 [kg]
weight engine cowling : 323.8 [kg]
weight thrust reversers : 186.8 [kg]
total weight propulsion system : 3554 [kg](6.8 [%])
***************************************************************
Accommodation cabin facilities :
UTA flew with the Caravelle 10B1R variant
typical 2-class cabin layout for 76 passengers : economy : pitch : 86.4 [cm] 34.0 [-in] ( 3+2 )
seating in 16.0 rows
first class pitch : 96.5 [cm] 38.0 [-in] at 4 -abreast
weight passenger seats (width 50.4 [cm]) : 495.0 [kg]
weight cabin crew seats : 15.0 [kg]
weight flight crew seats : 42.0 [kg]
high density seating passengers : 99 [pax] at mainly 5 -abreast seating in 20.5 rows, pitch
81.3 [cm] 32.0 [-in]
pax density, normal seating : 0.888 [m2/pax], high density seating : 0.682 [m2/pax]
weight 2 toilets : 56.2 [kg]
weight 2 galleys : 117.8 [kg]
weight overhead stowage for hand luggage (total : 5.3 [m3] = 111 55x35x25cm carry-on
trolleys) : 83.3 [kg]
weight 3 cloakrooms : 50.7 [kg]
Transeuropa Caravelle 10R EC-CIZ c/n 236 at Paris, Orly (ORY), June 1979. The 10R has 16 cabin windows at one side, the 10B has 18 cabin windows on one side.
weight 34 windows (41 x 28 cm) made of acrylic glass : 144.5 [kg]
weight 2 (1.69 x 0.91 [m]) main entry doors : 99.7 [kg]
weight 1 (1.22 x 0.61 [m]) crew/service doors : 24.1 [kg]
weight hydraulically-operated airstair for ventral entrance : 80.0 [kg]
weight 2 (main door size : 0.91 x 0.76 [m]) freight doors (belly) : 48.7 [kg]*
main/upper deck cabin holds for mail, accessories and luggage : 5.7 [m3]
usable belly baggage/cargo hold volume : 10.6 [m3]
passenger compartment volume : 82 [m3]
cabin volume (usable), excluding flight deck : 110 [m3]
passenger cabin max width : 3.00 [m] cabin length : 22.50 [m] max cabin height : 2.00 [m]
floor area : 60.0 [m2], cabin width at floor : 2.72 [m]
16.0 [%] of cabin floor area is occupied by toilets & galleys, the same at high density seating
weight cabin facilities : 1177.0 [kg]
safety facilities :
weight 4 type III over wing emergency exits (0.51 x 0.96 [m]): 69.1 [kg]
evacuation time with 99 passengers : 34 [sec]
weight 3 hand fire extinguisher : 8 [kg]
central aisle : 0.48 [m] wide
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators (deploy cabin alt.>4267m): 49.4 [kg]
weight emergency flare installation : 10 [kg]
weight 2 emergency evacuation slides : 36.8 [kg]
weight safety equipment & facilities : 274 [kg]
fuselage construction :
fuselage aluminium frame : 6597 [kg]
floor loading (payload/m2): 157 [kg/m2]
weight rear pressure bulkhead : 122.7 [kg]
fuselage covering ( 234.2 [m2] duraluminium 2.92 [mm]) : 1796.9 [kg]
weight paint fuselage : 49.2 [kg]
weight aluminium floor beams : 168.5 [kg]
weight cabin furbishing : 420.3 [kg]
weight cabin floor : 853.4 [kg]
weight (sound proof) isolation : 231.2 [kg] TO-noise level : 116.0 [EPNdB]
weight empty 71 [litre] potable water tanks : 6.2 [kg]
weight empty waste tank : 3.6 [kg]
weight engine mounts : 62 [kg]
weight fuselage structure : 10311.5 [kg]
Avionics :
weight HF/VHF radio and Selcal : 8.0 [kg]
weight Marconi Doppler and Bendix transponder : 7.0 [kg]
weight weather radar : 25.0 [kg]
weight ARINC 550 Automatic Direction Finding (ADF) equipment : 8.0 [kg]
weight ARINC 521D Distance Mesuring Equipment (DME) : 5.0 [kg]
weight Instrument Landing System (ILS/VOR) : 5.0 [kg]
weight Cat I minima DH 60m RVR >=600m landing system : 15.0 [kg]
weight artificial horizons, gyro-compass, radio altimeters : 7 [kg]
weight engine monitoring gauges & control switches : 14 [kg]
weight reserve ADI, ASI, alti-meter, compass, engine temp. and rpm indicators : 15 [kg]
weight avionics : 133.0 [kg]
Systems :
Air-conditioning and pressurization system maintains sea level conditions up to 6450 [m]
and gives equivalent of 2000 [m] at 11000 [m]. pressure differential : 0.58 [bar] (kg/cm2)
pressurized fuselage volume : 137 [m3] cabin air refreshment time : 2.6 [min]
weight air-conditioning and pressurization system : 89 [kg]
weight lighting : 25.1 [kg]
weight 175 [bar] hydraulic system : 13.5 [kg]
weight two 30V DC engine-driven generators and inverters for 115V 400 c/s AC : 19.0 [kg]
weight 22Ah battery : 28.5 [kg]
weight controls : 15.0 [kg]
weight systems : 190.0 [kg]
total weight fuselage : 12085 [kg](23.2 [%])
***************************************************************
wing construction :
total weight aluminium ribs (85 ribs) : 1769 [kg]
weight 4 wing fuel tanks empty for total 19000 [litre] fuel : 285 [kg]
weight 76 [litre] vent surge tanks : 9 [kg]
weight wing covering (painted aluminium 3.29 [mm]) : 2603 [kg]
total weight aluminium spars : 2626 [kg]
weight wings : 6998 [kg]
weight wing/square meter : 47.70 [kg]
weight bleed air thermal leading-edge anti-icing : 37.7 [kg]
weight ailerons (7.8 [m2]) : 187.6 [kg]
weight fin (10.0 [m2]) : 311.7 [kg]
weight rudder (5.5 [m2]) : 125.5 [kg]
weight tailplane (horizontal stabilizer) (21.5 [m2]): 567.0 [kg]
weight elevators (6.4 [m2]): 83.2 [kg]
weight paint wing & tail surfaces : 74.9 [kg]
weight flight control hydraulic servo actuators: 16.0 [kg]
weight trailing-edge single slotted Fowler flaps (24.7 [m2]) : 386.5 [kg]
weight spoilers (6.8 [m2]) : 85.6 [kg]
weight airbrakes (1.9 [m2]) : 28.5 [kg]
total weight wing construction : 9196 [kg] (31.6 [%])
*******************************************************************
landing gear :
tire pressure main wheels : 7.86 [Bar] (nitrogen), ply rating : 20 PR
tire speed limit : 364 [km/hr]
total tyre footprint : 0.13 [m2]
Runway LCN at MTOW (0.76m radius of rigidity) : 101 [ ]
Aircraft Classification Number (ACN), MTOW on rigid runway and medium subgrade
strength (B) : 27 [ ] Can also operate from unpaved runways subgrade B
wheel pressure : 5720.0 [kg]
wheel track 5.21 [m], wheelbase : 11.79 [m]
weight 8 Dunlop 35.0 x 9.0 main wheels (889 [mm] by 229 [mm]) : 614.0 [kg]
weight 2 nose wheels : 76.7 [kg]
weight heavy-duty hydraulic disc brakes : 45.3 [kg]
weight Hydro-air flywheel detector type anti-skid units : 9.0 [kg]
weight oleo-pneumatic shock absorbers : 51.3 [kg]
weight wheel hydraulic operated retraction system : 692.0 [kg]
weight undercarriage struts (four-wheel bogies) with axle 1937.0 [kg]
total weight landing gear : 3425.3 [kg] (6.6 [%]
*******************************************************************
********************************************************************
calculated empty weight : 28260 [kg](54.3 [%])
LTU Super Caravelle 10B1R D-ABAV c/n 243 at Palma de Mallorca, March 1978
aircraft equipment and service utensils :
weight oil for 4.3 hours flying : 21.9 [kg]
unusable fuel in engine and tanks 161.5 litre fuel : 126.8 [kg]
weight lifejackets : 34.2 [kg]
weight 1 life rafts : 47.5 [kg]
weight catering : 45.2 [kg]
weight water : 62.4 [kg]
weight crew : 405 [kg]
weight crew luggage, navigation chards, flight docs (NOTOC), manuals, miscellaneous items
: 71 [kg]
operational weight empty : 29075 [kg] (55.9 [%])
********************************************************************
useful load breakdown :
weight 76 passengers : 5852 [kg]
weight luggage : 1216 [kg]
weight cargo : 2357 [kg] (cargo + luggage/m3 belly : 165.0 [kg/m3])
zero fuel weight (ZFW): 38500 [kg](74.0 [%])
weight fuel for landing (3.2 hours flying) : 11000 [kg]
max. landing weight (MLW): 49500 [kg](95.2 [%])
max. landing weight higher than max. fuel weight makes it possible to make intermediate stops without refuelling
max. fuel weight : 43990 [kg] (84.6 [%])
payload with max fuel : 86 passengers + luggage 8010 [kg]
published maximum take-off weight : 52000 [kg] (100.0 [%])
CTA Compagnie de Transport Aerien Geneve Caravelle 10R HB-ICI c/n 250 at Faro, Portugal, 1988
calculation : * 4 * (engine power) :
power loading (Take-off) : 418 [kg/KN]
power loading (Take-off) 1 PUF: 835 [kg/KN]
max. total take-off power : 124.5 [KN]
calculation : *5* (loads) :
manoeuvre load : 1.6 [g] at 9000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.8 [g]
design flight time : 1.55 [hours]
design cycles : 33900 sorties, design hours : 52545 [hours]
max. wing loading (MTOW & flaps retracted) : 354 [kg/m2]
wing stress (2 g) during operation : 142 [N/kg] at 2g emergency manoeuvre
calculation : *6* (angles of attack) :
angle of attack zero lift : -1.75 ["]
max. angle of attack (stalling angle, clean) : 13.76 ["]
max. angle of attack (full flaps) : 13.60 ["]
UTA Union de Transports Aeriens Caravelle 10B1R F-BNRB c/n 222 at Palma de Mallorca, September 1970 .
angle of attack at economic cruise speed : 2.47 ["]
calculation : *7* (lift & drag ratios) :
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.22 [ ]
lift coefficient at max. angle of attack (clean): 1.33 [ ]
max. lift coefficient ( 40 [° ] flaps) : 1.50 [ ]
drag coefficient at max. speed : 0.0313 [ ]
drag coefficient at econ. cruise speed : 0.0351 [ ]
induced drag coefficient at econ. cruise speed : 0.0075 [ ]
drag coefficient (zero lift) : 0.0277 [ ]
lift/drag ratio at econ. speed : 7.11 [ ]
calculation : *8* (speeds) :
minimum control speed (Vmc): 231 [km/u] (124.8 [kt])
minimum unstick speed (Vmu) at TO angle 13.0 ° : 216 [km/u] (117 [kt])
take-off decision speed (V1) : 249 [km/u] (134 [kt])
take-off rotation speed (VR) : 253 [km/u] (136 [kt])
lift-off speed (VLOF) : 267 [km/u] (144 [kt]) at pitch angle : 7.4 [°]
take-off safety speed (V2) : 269 [km/u] (145 [kt])
flap retraction speed (V3) at 500m (OW loaded : 48579 [kg]): 253 [km/u] (137 [kt])
steady initial climb speed (V4) : 295 [km/u] (159 [kt])
climb speed (to FL150 with 80 [%] power) : 437 [km/hr] (236 [kt])
max. endurance speed (Vbe): 474 [km/u] min. fuel/hr : 2799 [kg/hr] at height : 8534 [m]
Hispania Caravelle 10R EC-CYI c/n 263
max. range speed (Vbr): 725 [km/u] (0.68 [mach]) min. fuel consumption : 4.46 [kg/km] at
cruise height : 10973 [m]
max. cruising speed : 800 [km/hr] (432 [kt]) at 10670 [m] (power:37 [%])
max. operational speed (Mmo) : 848 [km/hr] (Mach 0.76 ) at 7620 [m] (power:55 [%])
airflow at cruise speed per engine : 68.9 [kg/s]
speed of thrust jet : 2001 [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): 247 [km/u] (133 [kt])
stalling speed clean at 500 [m] height at Max.Landing Weight : 49500 [kg]): 235 [km/u] (127
[kt])
Special Air Transport Super Caravelle 10B1R D-ABAW c/n 239, landing at Dusseldorf, January 1985
final approach speed (landing speed) at sea-level with 40 [°] flaps VREF (max. landing
weight): 261 [km/u] (141 [kt])
ICAO Aircraft Approach Category (APC) : D
stalling speed at sea-level with 40 [°] flaps VSO (max. landing weight): 201 [km/u] (108 [kt]
stalling speed at sea-level with 40 [°] flaps VSO at 52000 [kg] AUW): 206 [km/u] (111 [kt]
rate of climb (max. continuous power) at sea-level ROC (loaded, 80 % power) : 760 [m/min]
rate of climb at sea-level ROC (loaded, 75 % power) : 675 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 80 % power on remaining engines)
: 59 [m/min]
Aero Lloyd Caravelle 10R D-ACVK c/n 176 at Faro, Portugal, 1988
rate of descent from FL240 to FL100 (7315m > 3048m): 1067 [m/min] (3501 [ft/min])
rate of descent during approach with landing gear extended, with use of spoilers: 265
[m/min] (4.4 [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 : 1884 [m]
Brake kinetic energy capacity : 747 [KW]
FAR TO runway length (TOFL) requirement at TOW 52000 [kg] standard day at SL (PUF
after V1): 1975 [m]
ICAO Aerodrome Reference Code : 3C Take-off flap setting : 20 [° ]
+++ FAA certification landing distance : +++
landing weight : 49500 [kg], TE flap setting : 40 [°]
runway condition : dry , landing over 50ft (15m) at threshold at sea-level
with use of thrust reversers, glideslope : 3.50 [°]
FAR landing field length ISA at SL, dry runway : 1614 [m] (5295 [ft])
FAR landing field length ISA at SL, wet runway: 1839 [m] (6034 [ft])
max. lift/drag ratio : 12.57 [ ]
climb to 5000 [m] with max payload : 6.09 [min]
climb to 10000 [m] with max payload : 18.73 [min]
Royal Jordanian Airlines Caravelle 10R JY-ACT c/n 200 at Nicosia (NIC) July 1970 .
descent time from 10000 [m] to 250 [m] : 24.33 [min]
max. ceiling fully loaded (mtow- 60 min.fuel): 48579 [kg] ) : 17500 [m]
ceiling limited by max. pressure differential 14250 [m]
max. theoretical ceiling (OWE + 60 min.fuel) : 19500 [m] with flying weight :32496 [kg]
calculation *10* (action radius & endurance) :
range with max. payload: 2940 [km] with 9425.0 [kg] max. useful load (90.5 [%] fuel)*
range with high density pax: 2990 [km] with 99 passengers (92.0 [%] fuel)*
range with typical two-class pax: 3299 [km] with 76 passengers (100.0 [%] fuel)*
range with max.fuel and MTOW : 3270 [km] with 5 crew and 86 passengers and 0 [kg]
cargo*
ferry range (calculated): 3525 [km] with 2 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 29651 [litre] fuel : 5305 [km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 296047 [paskm]
useful load with range 1000km : 9425 [kg]
useful load with range 1000km : 99 passengers
production (theor.max load): 7540 [tonkm/hour]
production (useful load): 7540 [tonkm/hour]
production (passengers): 79200 [paskm/hour]
none or very little cargo capability
oil and fuel consumption per tonkm : 0.454 [kg]
calculation *11* (operating cost) :
fuel cost per hour at econ.speed (4358 [litre]):2614 [eur] (17 [pax-km/litre fuel])
fuel cost per seat 1000km flight (99 [pax] 2-class seating): 35.21 [eur/1000PK]
oil cost per hour: 17 [eur]
crew cost per hour : 600 [eur]
list price 2024 : 67 [mln USD]
average flying hours in 1 year : 2150 [hours] technical life : 24 [year]
real average service life : 24 [years]
depreciation : 24 [years] to 10% residual value
financing interest per flying hour : 701 [EUR]
write off per flying hour : 1101 [EUR]
mean time between engine failure (MTBF) : 4988 [hr]
insufficient engine reliability for ETOPS flights
can continue fly on 1 engine, low risk for emergency landing for PUF
workhours per day : 8.74 [hr]
average flight hours till crash : 0.25 [mln hr] (118 service years)
safe flight hours till fatality : 6276 [hr] (2.9 service years)
reservation pax liability/flying hour : 20.52 [SDR*] (25.66 [eur])
insurance cost per hour : 1231 [eur] insurance rate : 5.3 [%]
engine maintenance cost per hour : 551.1 [eur]
wing maintenance cost per hour : 208.2 [eur]
fuselage maintenance cost per hour : 194.92 [eur]
tire life (time till worn out) : 149 [cycles]
maintenance cost per hour (excluding engines): 834 [eur]
direct operating cost per hour: 7674 [eur], DOC per km : 10.23 [eur]
DOC per seat 1000km flight (99 [pax] 2-class seating): 96.90 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 96.90 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 1.02 [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 : 3.54 [eur/pax]
airport landing fee / passenger : 3.54 [eur/pax]
retour ticket price 1000km trip : 275.87 [eur/pax]
price retour ticket Schiphol-Barcelona : 329.17 [eur/pax]
Transwede Caravelle 10R SE-DEC c/n 263. On 6 January 1987 it aboarded a take-off several seconds after lift-off from RW08 Stockholm-Arlanda apt. The aircraft landed hard with the main landing gears penetrating the wing, causing a fuel spill. A fire started but all 21 passengers and 6 crew could escape in time from the burning aircraft. Location : +- 100m 59°39’44”N 17°58’07”E
4 fatal accidents with a total of 161 fatalities > see the accident file
Literature :
wikipedia
Jane s all the world aircraft 1964-65 page 59
Jane s all the world aircraft 1970-71 page 40,41,42
KIJK straalverkeersvliegtuigen page 25
verkehrsflugzeuge page105
Air International okt’97 page 252
Praktisch handboek vliegtuigen deel 5 page 204
The Flier’s handbook page 81
Sud-Aviation SE 210 Caravelle - Wikipedia
Verkeersvliegtuigen page 9
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 28 March 2026 contact : info.aircraftinvestigation@gmail.com ac jetpax 2020.py python 3.7.4
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