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weight and performance calculations for the Vickers VC-10 type 1151
***** PRELIMINARY FILE ****
Vickers Super VC-10 G-ASGR landing at Wisley
Vickers VC-10 type 1151
importance : ****
first flight : 7 May 1964 (G-AGSA) operational : 1 April 1965 (BOAC, G-ASGD) LHR-JFK-SFO
country : United-Kingdom
design :
production : 22 aircraft (17 type 1151 and 5 type 1154)
general information :
The VC-10 1101 was specially developed for the BOAC, in order to attract other customers Vickers developed a new version with a larger range and capacity, which was more suitable for the transatlantic routes. The fuselage was extended by 8.5m and more powerful engines were installed. It received the designation VC 10 Super 200. The capacity was brought to 212 seats in a 2-class establishment. The BOAC ordered 10 aircraft in June 1960, the extension of the hull was reduced to 3.9m for the BOAC and the planned tip tanks were removed. It was given the new designation Super VC10.
In April 1965, the BOAC entered service with its first of 17 aircraft. For the EAA a passenger/cargo version was built, equipped with cargo door, designated as 1154, of which 5 were built.
The BOAC took the Super VC10 out of service in early 1981, together with the VC10 they had carried 13 million passengers over 901 million kilometers in 1,207,106 flight hours.
Five ex-BOAC Super VC-10s were converted into tankers for the RAF, designated VC-10 K.4 (type 1170), they entered service in 1994 and will remain in service into the 21st century.
Fuel : 69854 kg
primary users : BOAC, East African Airways (type 1154)
registrations : G-ASGC, G-ASGF,G-ASGN,G-ASGO,G-ASGR, 5X-UVA
Accommodation:
flight crew : 4 cabin crew : 5
flight crew consist of pilot, co-pilot, navigator and flight engineer
passengers : seating for 139 in two class : 12 business class and 127 economy class seats (32-in pitch)
high density seating for 174 passengers
engine : 4 Rolls Royce Rco.43 Conway 550 turbofan engines of 96.97 [KN](21799.4 [lbf])
dimensions :
wingspan : 44.55 [m], length : 52.32 [m], height : 12.04 [m]
wing area : 264.9 [m^2]
weights :
operating empty weight : 71155 [kg] max. structural payload : 26369 [kg]
Zero Fuel weight (ZFW) : 97524 [kg] max. landing weight (MLW) : 107503 [kg]
max.take-off weight : 151950 [kg] weight fuel : 70426 [kg] (88032 [litre])
performance :
Max. operating Mach number (Mmo) : 0.86 [Mach] (935 [km/hr]) at 9450 [m]
normal cruise speed : 886 [km/hr] (Mach 0.82 ) at 10000 [m] (35 [%] power)
service ceiling : 11000 [m]
range with max fuel : 7300 [km] and allowance for 862.4 [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 air foil : Vickers
sweep angle 3/4 chord: 32.5 [°]
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 : 0
calculation : *1* (dimensions)
mean wing chord : 5.95 [m]
calculated average wing chord tapered wing : 5.82 [m]
wing aspect ratio : 7.49 []
seize (span*length*height) : 28064 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 193.9 [kg/hr]
fuel consumption (econ. cruise speed) : 7530.3 [kg/hr] (9412.9 [litre/hr]) at 35 [%] power
distance flown for 1 kg fuel : 0.12 [km/kg] at 10000 [m] height, sfc : 56.1 [kg/KN/h]
total fuel capacity : 88032 [litre] (70426 [kg])
calculation : *3* (weight)
weight engine(s) dry : 8800.0 [kg] = 22.69 [kg/KN]
weight 2144.1 litre oil tank : 182.25 [kg]
G-ASGC BOAC Super VC-10
oil tank filled with 2.4 litre oil : 2.2 [kg]
oil in engine 64.8 litre oil : 58.2 [kg]
fuel in engine 47.6 litre fuel : 34.91 [kg]
weight fuel lines 88.0 [kg]
weight engine cowling 1163.6 [kg]
total weight propulsion system : 10329 [kg](6.8 [%])
***************************************************************
fuselage aluminium frame : 19250 [kg]
typical cabin layout for 139 passengers : average pitch : 81 [cm] ( 3+3 ) seating in 23.2 rows
pax density (normal seating) : 0.73 [m2/pax]
high density seating passengers : 173 at 6 -abreast seating in 28.8 rows, pitch 81 [cm]
weight 3 toilets : 48.2 [kg]
weight 7 hand fire extinguisher : 21 [kg]
weight 2 galleys : 160.3 [kg]
weight overhead stowage for hand luggage : 48.6 [kg]
weight 3 closets : 13.9 [kg]
weight 48 windows : 43.5 [kg]
weight 4 over wing emergency exits : 8.9 [kg]
weight lifejackets : 62.6 [kg]
weight oxygen masks & oxygen generators : 90.4 [kg]
weight emergency flare installation : 10 [kg]
weight 4 emergency evacuation slides : 39.0 [kg]
weight 4 entrance/exit doors : 48.0 [kg]
weight 2 freight doors (belly) : 8.0 [kg]
cabin volume (usable), excluding flight deck : 215.15 [m3]
passenger cabin max.width : 3.50 [m] cabin length : 32.03 [m] cabin height : 2.26 [m]
VC-10-1151 G-ASGN
floor area : 101.0 [m2]
pressure at cruise height 12192.00 [m] : 0.19 [kg/cm2] cabin pressure : 0.77 [kg/cm2]
weight rear pressure bulkhead : 258.7 [kg]
weight air pressurization system : 63.3 [kg]
fuselage covering ( 377.0 [m2] duraluminium 4.52 [mm]) : 4504.8 [kg]
weight floor beams : 583.1 [kg]
weight cabin furbishing : 677.3 [kg]
weight cabin floor : 1067.0 [kg]
fuselage (sound proof) isolation : 274.0 [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. : 38.0 [kg]
weight APU / engine starter: 48.5 [kg]
weight lighting : 34.8 [kg]
weight electricity generator : 34.8 [kg]
weight controls : 20.5 [kg]
weight seats : 740.0 [kg]
weight air conditioning : 208 [kg]
weight engine mounts : 194 [kg]
total weight fuselage : 28298 [kg](18.6 [%])
***************************************************************
The VC-10-1154 5X-UVA c/n 881 of East African Airways was lost on April 18, 1972 in an aborted takeoff. The aircraft finished 60m past the runway and caught fire on Addis Ababa. 43 people were killed. 1st flight : 1966 18586 flight hours. Intended to take off from RW07 for a 4416km long flight, no.720 from Addis Ababa(ADD) to Rome(FCO) with 96 passengers and 11 crew members.
Around V1, the nose wheel hit a metal part that a Cessna 185 had lost on the runway earlier that day. A tire broke and the crew decided to abort the takeoff, but they didn't stop in time. Location +-50m 8°58'55.96"N 38°49'03.18"E
EAA's VC10s were later converted into tankers for the RAF, designated VC-10 K.3 (type 1164)
total weight aluminium ribs (1305 ribs) : 5419 [kg]
weight fuel tanks empty for total 88032 [litre] fuel : 4930 [kg]
weight wing covering (painted aluminium 2.69 [mm]) : 3847 [kg]
total weight aluminium spars (multi-cellular wing structure) : 5136 [kg]
weight wings : 14402 [kg]
weight wing/square meter : 54.37 [kg]
weight rubber de-icing boots : 49.0 [kg]
weight fin & rudder (23.0 [m2]) : 1255.9 [kg]
weight stabilizer & elevator (29.8 [m2]): 1622.2 [kg]
weight flight control hydraulic servo actuators: 83.7 [kg]
weight fowler flaps (16.7 [m2]) : 458.9 [kg]
total weight wing surfaces & bracing : 22801 [kg] (15.0 [%])
*******************************************************************
wheel pressure : 16714.5 [kg]
The Super VC-10-1151 G-ASGN c/n 864 of the BOAC was blown up by the PLO on September 12, 1970 at Dawson's Field, Jordan after a hijacking. Was hijacked during a flight from Bahrain to Beirut on September 9. Location +-200m 32°06'21"N 36°09'36"E
Fortunately, the hostages were released.
weight 8 Dunlop main wheels (1130 [mm] by 174 [mm]) : 1662.5 [kg]
weight 2 Dunlop nose wheels : 207.8 [kg]
weight hydraulic wheel-brakes : 97.5 [kg]
weight pneumatic-hydraulic shock absorbers : 130.0 [kg]
weight wheel hydraulic operated retraction system : 1271.8 [kg]
weight undercarriage struts with axle 2926.0 [kg]
total weight landing gear : 6295.6 [kg] (4.1 [%]
*******************************************************************
********************************************************************
calculated empty weight : 67724 [kg](44.6 [%])
weight oil for 9.9 hours flying : 1917.5 [kg]
weight catering : 400.8 [kg]
weight water : 320.7 [kg]
weight crew : 729 [kg]
weight crew lugage,nav.chards,flight doc.,miscell.items : 63 [kg]
operational weight empty : 71155 [kg] (46.8 [%])
********************************************************************
weight 139 passengers : 10703 [kg]
weight luggage : 2224 [kg]
The VC-10-1151 G-ASGO c/n 865 was set on fire at Schiphol Airport, Amsterdam on 3 March 1974 after a hijacking. It was hijacked during a flight from Beirut (BEY) to London (LHR). Plane diverts to Schiphol. All 10 crew members and 100 passengers are released after which the hijackers pour flammable liquids on the cabin floor and set the plane on fire. The hijackers are caught as they run away from the plane. Location : +-100m 52°18'26"N 4°46'01"E.
weight cargo : 13442 [kg]
zero fuel weight (ZFW): 97524 [kg](64.2 [%])
weight fuel for landing (1.3 hours flying) : 9979 [kg]
max. landing weight (MLW): 107503 [kg](70.7 [%])
max. fuel weight : 141581 [kg] (93.2 [%])
payload with max fuel : 111 passengers+luggage 10369 [kg]
published maximum take-off weight : 151950 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 392 [kg/KN]
power loading (operational without useful load) : 334 [kg/kN]
power loading (Take-off) 1 PUF: 522 [kg/KN]
max. total take-off power : 387.9 [KN]
calculation : *5* (loads)
manoeuvre load : 5.7 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 0.9 [g]
design flight time : 5.77 [hours]
design cycles : 1961 sorties, design hours : 11308 [hours]
operational wing loading : 4796 [N/m^2]
wing stress (3 g) during operation : 265 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.77 ["]
max. angle of attack (stalling angle, clean) : 11.78 ["]
angle of attack at max. speed : 2.04 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.32 [ ]
lift coefficient at max. angle of attack : 1.15 [ ]
max. lift coefficient full flaps : 1.42 [ ]
induced drag coefficient at max.speed : 0.0058 [ ]
drag coefficient at max. speed : 0.0390 [ ]
drag coefficient (zero lift) : 0.0332 [ ]
lift/drag ratio at max. speed : 8.27 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 144420 [kg]): 314 [km/u]
stalling speed at sea-level with full flaps (normal landing weight): 243 [km/u]
landing speed at sea-level (normal landing weight : 107142 [kg]): 280 [km/hr]
max. rate of climb speed : 573 [km/hr] at sea-level
max. endurance speed : 365 [km/u] min. fuel/hr : 5516 [kg/hr] at height : 1219 [m]
max. range speed : 739 [km/u] min. fuel consumption : 8.615 [kg/km] at cruise height : 9144 [m]
cruising speed : 886 [km/hr] at 10000 [m] (power:32 [%])
max. operational speed (Mmo) : 935.00 [km/hr] (Mach 0.86 ) at 9450 [m] (power:38.5 [%])
airflow : 386.1 [kg/s]
speed of thrust jet : 2136 [km/hr]
climbing speed at sea-level (loaded) : 1723 [m/min]
climbing speed at 1000 [m] with 1 engine out (PUF / MTOW) : 1434 [m/min]
climbing speed at 1000 [m] with 2 engines out (2xPUF / MTOW) : 1380 [m/min]
BA G-ASGF
calculation : *9* (regarding various performances)
take-off speed : 386.4 [km/u]
high wheel pressure, can only take off from paved runways
take-off distance at sea-level concrete runway : 2322 [m]
take-off distance at sea-level over 15 [m] height : 2405 [m]
landing run : 1522 [m]
landing run from 15 [m] : 2510 [m]
lift/drag ratio : 11.65 [ ]
max. theoretical ceiling : 16400 [m] with flying weight :144420 [kg] line 3359
climb to 1000m with max payload : 0.67 [min]
climb to 2000m with max payload : 1.31 [min]
climb to 3000m with max payload : 1.92 [min]
climb to 5000 [m] with max payload : 3.01 [min]
minimum flying speed at 11000 [m] : 662 [km/hr]
theoretical ceiling fully loaded (mtow- 60 min. fuel:144420 [kg] ) : 16400 [m]
calculation *10* (action radius & endurance)
published range : 7300 [km] with 9 crew and 18751 [kg] useful load and 88.1 [%] fuel
range : 6404 [km] with 26369.0 [kg] max. useful load (77.3 [%] fuel)
range : 7985 [km] with 139.0 passengers with each 16 [kg] luggage and 96.4 [%] fuel
range max. fuel : 8286 [km] with 10369.4 [kg] useful load and 100.0 [%] fuel
Available Seat Kilometres (ASK) : 1109941 [paskm]
max range theoretically with additional fuel tanks total 100993.8 [litre] fuel : 9379 [km]
useful load with range 500km : 76545 [kg]
useful load with range 500km : 139 passengers
production (theor.max load): 67819 [tonkm/hour]
production (useful load): 23363 [tonkm/hour]
production (passengers): 123154 [paskm/hour]
combi aircraft mail/freight/passengers
oil and fuel consumption per tonkm : 0.114 [kg]
fuel cost per paskm : 0.063 [eur]
crew cost per paskm : 0.010 [eur]
time between engine failure : 626 [hr]
can continue fly on 3 engines, low risk for emergency landing for PUF
writing off per paskm : 0.040 [eur]
insurance per paskm : 0.0005 [eur]
maintenance cost per paskm : 0.034 [eur]
direct operating cost per paskm : 0.147 [eur]
direct operating cost per tonkm (max. load): 0.267 [eur]
direct operating cost per tonkm (normal useful load): 0.776 [eur]
Literature :
Wikipedia
Verkehrsflugzeuge page 29
Vickers VC10 | BAE Systems | International
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