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weight and performance calculations for the Ilyushin Il-62
CCCP-86682 c/n 90502 at Le Bourget, August 1974. The Kuznetsov NK-8-4
engine cowling difference little with the Il-62M, for this it can be distinguished
from the Il-62M.
Ilyushin Il-62
role : jet airliner
importance : ****
first flight : 3 January 1963 (CCCP-06156) operational : September 1967
country : Russia
NATO reporting name : CLASSIC
design : design team led by Sergei Ilyushin
production : 94 Il-62 aircraft at Kazan, total including 193 Il-62M and 5 prototypes : 292 aircraft
general information :
Designed to fly 7700 km (distance Moscow – New York) with more than 150 passengers and reserve fuel.
First flight was made with 73.55 [KN] Lyulka AL-7 turbojet engines, for the intended Kuznetsov NK-8-4 engines were not ready yet. At that moment it was the world largest jet airliner.
The prototype CCCP-06156 crashed on February 25, 1965 during a MTOW test flight. Couldn't
gain altitude after take-off and crashed, killing 10 of the 17 on board. The prototypes had two large blisters under the nose over the ends of emergency escape chutes for the pilots. Production aircraft didn’t have those chutes.
Early Il-62, looks like the prototype, CCCP-06156, without the nose probe
On September 15, 1967, it was deployed on the Moscow > Montreal route as a replacement for the Tu-114. July 1968 the route MOW > JFK is started.
In June 1965, the Il-62 (the third prototype CCCP-06176) was shown for the first time in the West, during the annual aviation exhibition at Le Bourget.
3 e prototype CCCP-06176 at Le Bourget, June 1965, getting a lot of attention. Early
Il-62 had a fearing below the nose.
In 1966 and 1967, the Il-62 was already in service on the domestic Aeroflot
network. On September 15, 1967, it was used for the first time on an
international route, namely that from Moscow to Montreal.
Flying controls are operated manually, which is remarkable for so a large aircraft. It has an automatic flight control system that can take-over from 200m height after take-off till the same height upon landing. It can maintain a preset speed and course.
The Il-62 is almost identical in size and engine power to the British VC-10.
De Il-62 was designed for 25.000 – 30.000 flying hours and 7000 – 8000
cycles.
primary users : Aeroflot, CSA (7), Interflug (6), LOT (5), CAAC (5), Tarom (3), Cubana (1)
Accommodation:
flight crew : 5 cabin crew : 7
flight crew consist of captain, first officer, flight engineer and optionally a navigator and a radio officer
passengers : seating for 150 in two class : 12 business class and 138 coach class
seats ( 34 -in pitch) high density seating for 186 passengers
engine : 4 Kuznetsov NK-8-4 turbofan engines of 103.0 [KN] (23154.9 [lbf])
Aeroflot CCCP-06176, Il-62 third prototype.
Measured chord at root : 10.87 [m] at tip : 2.51 [m] length of fuselage : 48.69 [m]
dimensions :
wingspan : 43.2 [m], length overall: 53.12 [m], height : 12.35 [m]
wing area : 279.6 [m^2] fuselage exterior width : 4.1 [m]
weights :
empty weight : 66400 [kg]
operating empty weight : 69400 [kg] max. structural payload : 24100 [kg]
Zero Fuel weight (ZFW) : 93500 [kg] max. landing weight (MLW) : 105000 [kg]
max.take-off weight : 162000 [kg] weight fuel : 83325 [kg] (104156 [litres])
performance :
Max. operating Mach number (Mmo) : 0.84 [Mach] (900 [km/hr]) at 10000 [m]
critical Mach speed : 0.88 [Mach]
max. cruising speed : 870 [km/hr] (Mach 0.81 ) at 10500 [m] (35 [%] power)
economic cruising speed : 850 [km/hr] (Mach 0.80 ) at 10500 [m]
service ceiling : 13000 [m]
range with max fuel and Max.TOW : 9200 [km] (ATA domestic fuel reserves - 820.0 [km] alternate)
description :
cantilever low-wing monoplane with retractable landing gear with nose wheel
Wings : all-metall three-spar fail-safe wing structure
Line-up of Il-62’s, CCCP-86679 in the back ground
with double slotted trailing edge flaps, with extended chord "dog-tooth" leading edge on outer two-thirds on each wing, acting as an aerodynamic fence vortex generator and fixed leading edge droop for better control at high angles off attack, to prevent "deep stall" and improved long-range cruise efficiency ,with spoilers airfoil : Ilyushin
sweep angle 3/4 chord: 35.0 [°]
engines attached to the tail, landing gear attached to the wings, fuel tanks in the wings and wing center section
Fuselage : Pressurized conventional all-metal semi-monocoque fail safe structure of circular section
calculation : *1* (dimensions)
measured wing chord at root: 10.87 [m]
measured wing chord at tip : 2.51 [m]
taper ratio : 0.231 [ ]
mean wing chord : 6.47 [m]
calculated average wing chord tapered wing with rounded tips: 6.52 [m]
wing aspect ratio : 6.67 []
Oswald factor (e): 0.677 []
seize (span*length*height) : 28341 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 12.4 [kg/hr]
fuel consumption (econ. cruise speed) : 7068.5 [kg/hr] (8835.6 [litre/hr]) at 22 [%] power
distance flown for 1 kg fuel : 0.12 [km/kg] at 10500 [m] height, sfc : 77.0 [kg/KN/h]
total fuel capacity : 104156 [litre] (83325 [kg])
calculation : *3* (weight)
weight engine(s) dry : 9600.0 [kg] = 23.30 [kg/KN]
weight 204.1 litre oil tank : 17.35 [kg]
oil tank filled with 2.6 litre oil : 2.3 [kg]
oil in engine 5.0 litre oil : 4.5 [kg]
fuel in engine 22.5 litre fuel : 16.48 [kg]
weight fuel lines : 324.0 [kg]
weight engine cowling : 1071.2 [kg]
weight double thrust reversers : 700.4 [kg]
total weight propulsion system : 11736 [kg](7.2 [%])
***************************************************************
Accommodation cabin facilities:
typical 2-class cabin layout for 150 passengers : economy : pitch : 86.4 [cm] 34.0 [-in]
( 3+3 ) seating in 25.4 rows
weight seats : 810.0 [kg]
high density seating passengers : 186 [pax] at 6 -abreast seating in 31.0 rows, pitch
86.4 [cm] 34.0 [-in]
pax density, normal seating : 0.76 [m2/pax], high density seating : 0.61 [m2/pax]
weight 5 lavatories : 72.9 [kg]
weight 5 galleys : 270.0 [kg]
weight overhead stowage for hand luggage : 52.5 [kg]
weight 2 wardrobe closets : 30.0 [kg]
weight 53 windows (47x38cm) : 47.5 [kg]
Interior of Interflug Il-62 DDR-SEG c/n 31403. This aircraft was in service
from 1973 till 1989. It is on display on the grass strip at Stolln-Rhinow
weight 3 (1.83 x 0.86 [m]) main entry doors : 154.3 [kg]
weight 1 (1.37 x 0.61 [m]) service doors : 27.3 [kg]
weight 3 (1.31 x 1.26 [m]) freight doors (belly) : 135.2 [kg]
total belly baggage/cargo hold volume : 44.82 [m3]
cabin volume (usable), excluding flight deck : 250 [m3]
passenger compartment volume : 163 [m3]
passenger cabin max.width : 3.49 [m] cabin length : 36.87 [m] cabin height : 2.12 [m]
floor area : 113.6 [m2]
weight cabin facilities : 1599.8 [kg]
safety facilities:
weight 4 over wing emergency exits (90x48 cm): 64.1 [kg]
evacuation time with 186 passengers : 49 [sec]
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 : 139.8 [kg]
weight safety equipment & facilities : 456 [kg]
fuselage construction:
fuselage aluminium frame : 13427 [kg]
floor loading (payload/m2): 212 [kg/m2]
weight rear pressure bulkhead : 181.4 [kg]
fuselage covering ( 472.4 [m2] duraluminium 3.19 [mm]) : 3985.3 [kg]
weight floor beams : 630.3 [kg]
weight cabin furbishing : 955.8 [kg]
weight cabin floor : 1764.7 [kg]
weight (sound proof) isolation : 343.7 [kg]
weight 40330 [litre] main central fuel tanks empty : 2258.5 [kg]
weight empty 203 [litre] potable water tank : 18.0 [kg]
weight empty waste tank : 18.3 [kg]
weight engine mounts : 206 [kg]
weight fuselage structure : 23788.6 [kg]
Avionics:
weight VHF radio and Selcal : 9.0 [kg]
weight flight and service attendants intercom : 5.0 [kg]
cockpit Il-62 CCCP-86698, the aircraft was on display in Kiev, at the old city airport Zhulyany. Due to the 2022 Russian – Ukrainian war, I wonder if it is still there intact.
weight dual cloud-collision radar : 25.0 [kg]
weight weather radar : 25.0 [kg]
weight VOR/ILS,RMI,DME,radio altimeter : 12.0 [kg]
weight automatic flight control System / auto-pilot : 23.0 [kg]
weight artificial horizons, compass, alti-meters : 7 [kg]
weight engine monitoring gauges & control switches : 12 [kg]
weight avionics : 99.0 [kg]
Systems:
Air-conditioning and pressurization system maintains sea level conditions up to
7350 [m] and gives equivalent of 2100 [m] at 13000 [m]. pressure differential : 0.63
[bars] (kg/cm2)
pressurized fuselage volume : 396 [m3]
weight air-conditioning and pressurization system : 218 [kg]
weight APU / engine starter: 51.5 [kg]
weight lighting : 49.5 [kg]
weight 210 bar hydraulic system : 95.8 [kg]
weight engine-driven 40kVA electricity generators : 37.5 [kg]
weight 22Ah battery : 12.0 [kg]
weight controls : 21.6 [kg]
weight systems : 485.9 [kg]
total weight fuselage : 26430 [kg](16.3 [%])
***************************************************************
average Take-off weight : 121774 [kg](75.2 [%])
CAAC Il-62 B-2022 c/n 11005, March 1980 at Shanghai-Hongqiao
total weight aluminium ribs (1120 ribs) : 5060 [kg]
weight 6 wing fuel tanks empty for total 63826 [litre] fuel : 3574 [kg]
weight wing covering (painted aluminium 2.76 [mm]) : 4167 [kg]
total weight aluminium spars (multi-cellular wing structure) : 6158 [kg]
weight wings : 15384 [kg]
weight wing/square meter : 55.02 [kg]
weight thermal leading-edge anti-icing : 47.5 [kg]
weight ailerons (16.24 [m2]) : 448.1 [kg]
weight fin (27.49 [m2]) : 986.0 [kg]
weight rudder (10.50 [m2]) : 278.0 [kg]
weight tailplane (stabilizer) (32.14 [m2]): 975.2 [kg]
weight elevators (7.71 [m2]): 114.90 [kg]
weight flight control hydraulic servo actuators: 47.2 [kg]
weight trailing-edge double slotted flaps (43.49 [m2]) : 1022.2 [kg]
weight spoilers (9.5 [m2]) : 133.0 [kg]
total weight wing construction : 23010 [kg] (33.2 [%])
*******************************************************************
tire pressure main wheels : 9.50 [Bar] (nitrogen), ply rating : 23 PR
tire speed limit : 364 [km/hr]
total tyre footprint : 1.10 [m2]
Aircraft Classification Number, MTOW on rigid runway and medium subgrade strength (B) : 20 [ ]
good soft ground capabilities
Tarom Il-62 YR-IRB
wheel pressure : 17820.0 [kg]
weight 8 main wheels (1450 [mm] by 450 [mm]) : 1446.8 [kg]
weight 2 nose wheels : 180.9 [kg]
weight multi-disc wheel-brakes : 93.5 [kg]
weight Hydro-air flywheel detector type anti-skid units : 9.0 [kg]
weight oleo-pneumatic shock absorbers : 124.7 [kg]
weight wheel hydraulic operated retraction system : 1302.4 [kg]
Il-62 CCCP-86677 c/n 80402 at Le Bourget, 1972. Note the extended tail support strut.
weight hydraulic operated twin-wheel tail support parking strut : 80 [kg]
weight undercarriage struts (four-wheel bogies) with axle 3209.6 [kg]
total weight landing gear : 6446.8 [kg] (4.0 [%]
*******************************************************************
********************************************************************
calculated empty weight : 67623 [kg](41.7 [%])
weight oil for 12.7 hours flying : 175.4 [kg]
weight lifejackets : 67.5 [kg]
weight 3 life rafts : 93.8 [kg]
weight catering : 225.0 [kg]
weight water : 180.0 [kg]
weight crew : 972 [kg]
weight crew lugage,nav.chards,flight doc.,miscell.items : 63 [kg]
operational weight empty : 69400 [kg] (42.8 [%])
********************************************************************
weight 150 passengers : 11550 [kg]
weight luggage : 2400 [kg]
weight cargo : 10150 [kg] (cargo+luggage/m3 belly : 267 [kg/m3])
zero fuel weight (ZFW): 93500 [kg](57.7 [%])
weight fuel for landing (1.6 hours flying) : 11500 [kg]
max. landing weight (MLW): 105000 [kg](64.8 [%])
max. fuel weight : 152725 [kg] (94.3 [%])
payload with max fuel : 100 passengers+luggage 9275 [kg]
published maximum take-off weight : 162000 [kg] (100.0 [%])
Il-62 prototype CCCP-06176 on display at Le Bourget, Paris Air Salon, 1965
calculation : * 4 * (engine power)
power loading (Take-off) : 393 [kg/KN]
power loading (Take-off) 1 PUF: 524 [kg/KN]
max. total take-off power : 412.0 [KN]
calculation : *5* (loads)
manoeuvre load : 6.8 [g] at 1000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 0.9 [g]
design flight time : 3.00 [hours]
design cycles : 12100 sorties, design hours : 36300 [hours]
max. wing loading (MTOW & flaps retracted) : 579 [kg/m2]
wing stress (2 g) during operation : 170 [N/kg] at 2g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.84 ["]
max. angle of attack (stalling angle, clean) : 13.86 ["]
max. angle of attack (full flaps) : 13.06 ["]
angle of attack at max. speed : 2.61 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.36 [ ]
lift coefficient at max. angle of attack : 1.28 [ ]
max. lift coefficient full flaps : 1.59 [ ]
drag coefficient at max. speed : 0.0289 [ ]
drag coefficient at econ. cruise speed : 0.0304 [ ]
induced drag coefficient at econ. cruise speed : 0.0107 [ ]
drag coefficient (zero lift) : 0.0196 [ ]
lift/drag ratio at econ. speed : 12.55 [ ]
calculation : *8* (speeds
take-off decision speed (V1) : 264 [km/u] (142 [kt])
lift-off speed (VLOF) : 290 [km/u] (156 [kt])
take-off safety speed (V2) : 306 [km/u] (165 [kt])
steady initial climb speed (V4) : 332 [km/u] (179 [kt])
Il-62 prototype CCCP-06156, flying without probe in the nose
flap retraction speed (V3) at 500m (OW loaded : 154932 [kg]): 324 [km/u] (175 [kt])
climb speed (to FL150 with 63 [%] power) : 605 [km/hr] (327 [kt])
max. endurance speed (Vbe): 583 [km/u] min. fuel/hr : 6759 [kg/hr] at height : 6706 [m]
max. range speed (Vbr) = economic cruise speed : 850 [km/u] min.fuel cons. : 8.316 [kg/km] at cruise height : 10500 [m]
max. cruising speed : 870 [km/hr] (470 [kt]) at 10500 [m] (power:23 [%])
max. operational speed (Mmo) : 900 [km/hr] (Mach 0.84 ) at 10000 [m] (power:24 [%])
airflow at cruise speed per engine : 153.0 [kg/s]
speed of thrust jet : 1418 [km/hr]
initial descent speed 10000 - 7315 [m]: Mach 0.82
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): 265 [km/u] (143 [kt])
final approach speed (landing speed) at sea-level with full flaps VREF (max. landing weight): 268 [km/u] (145 [kt])
ICAO Aircraft Approach Category (APC) : D
stalling speed at sea-level with full flaps VSO (max. landing weight): 206 [km/u]
rate of climb at sea-level ROC (loaded, 63 % power) : 1082 [m/min]
rate of climb at sea-level ROC (loaded, 75% power) : 1471 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 100 % power on remaining engines) : 2288 [m/min]
rate of climb at 1000 [m] with 2 engines out (2xPUF / MTOW) : 1286 [m/min]
rate of descent from FL240 to FL100 (7315m > 3048m): 914 [m/min] (2999 [ft/min])
rate of descent during approach with landing gear extended, with use of spoilers: 457 [m/min] (1499 [ft/min])
calculation : *9* (regarding various performances)
low wheel pressure, can also take off from unpaved runways
take-off distance at sea-level concrete runway : 2817 [m]
ICAO Aerodrome Reference Code : 4D
take-off distance (C.A.R) at sea-level over 10.7 [m] height : 2917 [m]
FAR TO runway length requirement at MTOW, standard day at SL (ASDA): 3250 [m]
landing run (MLW) : 991 [m]
landing distance (C.A.R.) from 15 [m] at SL, dry runway : 1930 [m]
landing distance (C.A.R.) from 15 [m] at SL, wet runway : 2230 [m]
LOT Il-62 SP-LAC c/n 31401
FAR landing runway length requirements at SL : 2304 [m]
max. lift/drag ratio : 13.44 [ ]
climb to 5000 [m] with max payload : 4.28 [min]
climb to 10000 [m] with max payload : 13.16 [min]
descent time from 10000 [m] to 250 [m] : 24.33 [min]
ceiling limited by max. pressure differential 17025 [m]
theoretical ceiling fully loaded (mtow- 60 min.fuel: 154932 [kg] ) : 15600 [m]
calculation *10* (action radius & endurance)
range with max. payload: 7883 [km] with 24100.0 [kg] max. useful load (82.2 [%] fuel)*
range with high density pax: 8843 [km] with 186 passengers (90.4 [%] fuel)*
range with typical two-class pax: 9328 [km] with 150 passengers (94.4 [%] fuel)*
range with max.fuel : 10020 [km] with 12 crew and 100 passengers and 100.0 [%] fuel*
ferry range : 10633 [km] with 5 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 116965 [litre] fuel : 11594 [km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 1661227 [paskm]
useful load with range 1000km : 24100 [kg]
useful load with range 1000km : 186 passengers
production (theor.max load): 20967 [tonkm/hour]
production (useful load): 20967 [tonkm/hour]
production (passengers): 161820 [paskm/hour]
oil and fuel consumption per tonkm : 0.338 [kg]
calculation *11* (operating cost)
fuel cost per hour (8836 [litre]):5301 [eur] (18 [pax-km/litre fuel])
fuel cost per seat 1000km flight (186 [pax] 2-class seating): 32.76 [eur/1000PK]
oil cost per hour: 52 [eur]
crew cost per hour : 1650 [eur]
list price 2023 : 152 [mln USD]
average flying hours in 1 year : 1500 [hours] technical life : 24 [year]
real average service life : 15 [years]
economic hours (average real flown hours): 22500 [hours] is 38 [%] less then design hours
financing interest per flying hour : 2369 [EUR]
write off per flying hour : 5832 [EUR]
time between engine failure : 10354 [hr]
can continue fly on 3 engines, low risk for emergency landing for PUF
workhours per day : 5.14 [hr]
average flight hours till crash : 0.42 [mln hr] (282 service years)
Aeroflot CCCP-86613 c/n 51901 was written off after an emergency landing on 21 November 1990 at Yakutsk-Magan airport. On a flight from Moscow to Yakutsk, with 179 passengers and 10 crew it had to divert to Magan apt. due to bad weather. It landed halfway the runway in snowy conditions. It was not able to stop in time and ran off the runway, it landing gear broke off and then the aircraft came to rest 538m past the RW. There were no fatalities. The tail is all that is left of the aircraft, but it gives an insight in the IL-62 construction.
Location: +- 500m : 62°05’38”N 129°32’55”E
safe flight hours till fatality : 3825 [hr] (2.5 service years)
reservation pax liability/flying hour : 33.68 [SDR*] (42.10 [eur])
insurance cost per hour : 398 [eur]
engine maintenance cost per hour : 215.2 [eur]
wing maintenance cost per hour : 205.0 [eur]
fuselage maintenance cost per hour : 104.98 [eur]
tire life (time till worn out) : 104 [cycles]
maintenance cost per hour (excluding engines): 1238 [eur]
direct operating cost per hour: 17097 [eur]
DOC per seat 1000km flight (186 [pax] 2-class seating): 105.65 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 105.65 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 0.82 [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 : 5.20 [eur/pax]
airport landing fee / passenger : 5.20 [eur/pax]
retour ticket price 1000km trip : 302.44 [eur/pax]
price retour ticket Schiphol-Barcelona : 360.55 [eur/pax]
accidents with fatalities > see the accident file
Notes : lowest wheelpressure/M3 of its category with 229 KN/m3
Highest ticket price AMS-BCN : 360.55 EUR
Il-62 CCCP-86690 was delivered to Aeroflot September 1971.
Literature :
Jane’s all the world aircraft 1964-’65 page 318
Bekende vliegtuigen van Rusland en Italië page 87
Sowiet engines page 9
Waarom vloog de KLM met Ilyushin Il-62's? - Up in the Sky
Jane’s commercial transport aircraft page 167
How Air France in 1968 flew the Soviet Il-62 | flight attendant | Zen (dzen.ru)
Verkeersvliegtuigen page 55
The flier’s handbook page 113
http://foto-i-mir.ru/il-62/
Jane’s all the world aircraft 1979-1980 page185
Jane’s all the world aircraft 1970-71 page
Verkeersvliegtuigen (Moussault) page 90,158
Aviation Disasters/D.Gero
Alles over Russische vliegtuigen page 93
Heritage Special: The Il-62, Russia's First Long Haul Jetliner - SamChui.com
AFC - Aviation Fan Club (aviation-fan-club.com)
"We landed," he said, and died. Only two survived the CSA crash 36 years ago - iDNES.cz
The Secret Tragedy of csa flight | News | Tiscali.cz
https://contentzone.eurocontrol.int/aircraftperformance/default.aspx?
United Arab Airlines Ilyushin Il-62 SU-ARO c/n 00705, July 1971 at Rome Fiucimo airport
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 08 October 2023 contact : info.aircraftinvestigation@gmail.com ac jetpax 2020.py python 3.7.4
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