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weight and performance calculations for the Tupolev Tu-104A CAMEL
***** PRELIMINARY FILE ****
Tu-104A OK-LDA van de CSA
Tupolev Tu-104A
importance : ****
first flight : 1957 operational : May 1958
country : USSR
NATO reporting name : CAMEL
design :
production : 80 aircraft
general information :
Pretty much the same as the Tu-104, only the interior was changed and it had more powerful engines. Aspect ratio : 6.5 t/c ratio : 12%. Max.differential pressure : 0.5 kg/cm^2. Vapproach : 267 km/h. The Tu104A could fly non-stop from Amsterdam to Moscow. It was first shown to the public in June 1957. Immediately a number of records were set. On 6 September 1957, 20053 kg was raised to 2000m altitude, an altitude of 11221m was reached and on 24 September 1957 a speed record of 970 km/h at 2000m over a closed circuit of 1000km.
Fuselage diameter : 3.50m cabin width :3.20m height cabin : 2.10m
Cargo hold (belly) : 28m3
primary users : Aeroflot, CSA
Accomodation:
flight crew : 3 cabin crew : 3
flight crew consist of pilot, co-pilot and flight engineer
passengers : seating for 70 in two class : 20 business class and 50 economy class seats ( 32 -in pitch)
engine : 2 Mikoelin AM-3M turbojet engines of 85.43 [KN](19205.1 [lbf])
dimensions :
wingspan : 34.54 [m], length : 38.85 [m], height : 11.53 [m]
wing area : 187.95 [m^2]
Cabin seat arrangement Tu-104A, standard seating for 70 passengers
weights :
operating empty weight : 40000 [kg] max. structural payload : 12000 [kg]
Zero Fuel weight (ZFW) : 52000 [kg] max. landing weight (MLW) : 64000 [kg]
max.take-off weight : 75500 [kg] weight fuel : 27180 [kg] (33975 [liter])
performance :
Max. operating Mach number (Mmo) : 0.91 [Mach] (970 [km/hr]) at 10700 [m]
normal cruise speed : 840 [km/hr] (Mach 0.77 ) at 9000 [m] (39 [%] power)
service ceiling : 11211 [m]
range with max fuel : 3239 [km] and allowance for 320.6 [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 : NACA
sweep angle 3/4 chord: 37.0 [°]
engines in the wingroot and landing gear attached to the wings, fuel tanks in the wings and fuselage
construction : all-metal aluminium-alloy stressed-skin construction with pressurized fuselage
fuselage shape : 0
calculation : *1* (dimensions)
measured wing chord : 5.70 [m] at 50% wingspan
mean wing chord : 5.44 [m]
calculated average wing chord tapered wing with rounded tips: 5.46 [m]
wing aspect ratio : 6.35 []
seize (span*length*height) : 15472 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 85.4 [kg/hr]
fuel consumption (econ. cruise speed) : 6210.5 [kg/hr] (7763.1 [litre/hr]) at 39 [%] power
distance flown for 1 kg fuel : 0.14 [km/kg] at 9000 [m] height, sfc : 93.2 [kg/KN/h]
total fuel capacity : 33975 [litre] (27180 [kg])
August 15, 1958, the Tu-104A CCCP-L5442 (CCCP42349) of the Aeroflot crashes near Chita. flt Khabarovsk (KHV) > Irkutsk (IKT). ac was given permission to fly over an area of thunderstorms. ac climbed to 12,000m but suddenly got into a vertical airflow. This caused it to stall where the bem could no longer get out. All 53 passengers and 11 crew members are killed. c/n 7350303 first
flight : 1957 2 Mikulin AM-3M engines. Location : +-10km 52°01'40"N 113°57'35"E
calculation : *3* (weight)
weight engine(s) dry : 6200.0 [kg] = 36.29 [kg/KN]
weight 443.9 litre oil tank : 37.73 [kg]
oil tank filled with 1.1 litre oil : 1.0 [kg]
oil in engine 28.5 litre oil : 25.6 [kg]
fuel in engine 21.0 litre fuel : 15.38 [kg]
weight fuel lines 34.0 [kg]
weight engine cowling 512.6 [kg]
total weight propulsion system : 6826 [kg](9.0 [%])
***************************************************************
fuselage aluminium frame : 10513 [kg]
typical cabin layout for 70 passengers : economy : pitch : 81 [cm] ( 3+2 ) seating in 15.0 rows
pax density (normal seating) : 1.14 [m2/pax]
high density seating passengers : 98 at 5 -abreast seating in 19.6 rows, pitch 76 [cm]
weight 2 toilets : 36.6 [kg]
weight 4 hand fire extinguisher : 10 [kg]
weight 1 galleys : 60.5 [kg]
weight overhead stowage for hand luggage : 24.5 [kg]
On October 17, 1958, another serious accident occurred with a Tu-104A. Flight from Beijing (PEK) via Omsk (OMS) to Moscow (MOW), LOC at 30,000ft. crash 650km east of Moscow, 20km west of Kanash. Crosses at 11,000m, gets into severe turbulence and gets into stall where crew could not get out. Situation almost identical as in the case of a disaster on 15 Aug. The pilot described over the radio exactly what happened until his last goodbye word. This information turned out to be very useful for the investigation into the cause. It turned out that the Tu-104 reacted very slowly to the manual control. The autopilot did not function well when tilting at high altitude. The stabilizers were adjusted and additional position instruments were installed that complemented the artificial horizon. Could not land on MOW due to dense fog,rerouted course to Sverdlovsk. Reg : CCCP-42362. c/n 86601002. All 71 passengers and 9 crew members are killed. Location : +-2km 55°29'18.90"N 47°09'54.25"E first flight : 1958, AM-3M engines.
weight 1 closets : 7.0 [kg]
weight 32 windows : 28.8 [kg]
weight 2 overwing emergency exits : 4.5 [kg]
weight 4 life rafts : 87.5 [kg]
weight oxygen masks & oxygen generators : 45.5 [kg]
weight emergency flare installation : 10 [kg]
weight 2 emergency evacuation slides : 18.4 [kg]
weight 2 entrance/exit doors : 24.0 [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 : 156.01 [m3]
passenger cabin max.width : 3.20 [m] cabin length : 27.78 [m] cabin height : 2.10 [m]
floor area : 80.1 [m2]
pressure difference : 0.50 [kg/cm2]
weight rear pressure bulkhead : 135.5 [kg]
From Tu-104A CCCP-42398 van from Aeroflot
Tu-104A CCCP-42370 of the Aeroflot crashed on June 30, 1962 near Krasnoyarsk. c/n 86601301. All 76 passengers and 8 crew members are killed. Domestic flight from Irkutsk(IKT) to Omsk(OMS), crosses at 9000m gets into a nosedive and crashed. Would have been shot down by accident by a SAM, during an air defense exercise in the Magansk region. Crashed in forest near Voznesenka, killing everyone on board. According to some sources, registration is 42340, but I can't find a c/n of this and seems incorrect. Location : +-20km 57°21'25"N 91°47'28"E 1st flight : 1958 2 AM-3M engines. No pictures found of this aircraft.
weight air pressurization system : 46.7 [kg]
fuselage covering ( 309.7 [m2] duraluminium 2.83 [mm]) : 2328.6 [kg]
weight floor beams : 268.4 [kg]
weight cabin furbishing : 355.4 [kg]
weight cabin floor : 645.0 [kg]
fuselage (sound proof) isolation : 263.7 [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: 42.7 [kg]
weight lighting : 17.5 [kg]
weight electricity generator : 17.5 [kg]
weight controls : 15.7 [kg]
weight seats : 380.0 [kg]
weight 16988 [litre] main central fuel tanks empty : 951.3 [kg]
weight air conditioning : 105 [kg]
total weight fuselage : 16218 [kg](21.5 [%])
***************************************************************
total weight aluminium ribs (709 ribs) : 2692 [kg]
weight engine mounts : 85 [kg]
weight fuel tanks empty for total 16988 [litre] fuel : 951 [kg]
weight wing covering (painted aluminium 2.57 [mm]) : 2610 [kg]
total weight aluminium spars (multi-cellular wing structure) : 3544 [kg]
weight wings : 8847 [kg]
weight wing/square meter : 47.07 [kg]
weight rubber de-icing boots : 38.0 [kg]
weight fin & rudder (13.8 [m2]) : 653.9 [kg]
weight stabilizer & elevator (21.1 [m2]): 996.7 [kg]
weight flight control hydraulic servo actuators: 43.6 [kg]
weight fowler flaps (11.4 [m2]) : 275.1 [kg]
total weight wing surfaces & bracing : 11891 [kg] (15.7 [%])
*******************************************************************
wheel pressure : 8305.0 [kg]
weight 8 Dunlop main wheels (1130 [mm] by 226 [mm]) : 1074.0 [kg]
weight 8 Dunlop main wheels (1130 [mm] by 226 [mm]) : 1074.0 [kg]
weight 2 Dunlop nose wheels : 134.3 [kg]
weight hydraulic wheel-brakes : 52.0 [kg]
weight pneumatic-hydraulic shock absorbers : 69.3 [kg]
weight wheel hydraulic operated retraction system : 801.9 [kg]
weight undercarriage struts with axle 1837.8 [kg]
total weight landing gear : 3969.3 [kg] (5.3 [%]
*******************************************************************
********************************************************************
calculated empty weight : 38904 [kg](51.5 [%])
weight oil for 4.6 hours flying : 395.3 [kg]
weight catering : 108.0 [kg]
weight water : 43.2 [kg]
weight crew : 486 [kg]
weight crew lugage,nav.chards,flight doc.,miscell.items : 64 [kg]
operational weight empty : 40000 [kg] (53.0 [%])
********************************************************************
weight 70 passengers : 5390 [kg]
weight luggage : 1120 [kg]
weight cargo : 5490 [kg]
zero fuel weight (ZFW): 52000 [kg](68.9 [%])
weight fuel for landing (1.9 hours flying) : 12000 [kg]
max. landing weight (MLW): 64000 [kg](84.8 [%])
max. fuel weight : 67180 [kg] (89.0 [%])
payload with max fuel : 89 passengers+luggage 8320 [kg]
published maximum take-off weight : 75500 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 442 [kg/KN]
power loading (operational without useful load) : 408 [kg/kN]
power loading (Take-off) 1 PUF: 884 [kg/KN]
high powerloading if engine failure, can not stay airborne
max. total take-off power : 170.9 [KN]
On September 2, 1962, the Tu-104A CCCP42366 crashed 10 min after TO Khabarovsk apt. Aeroflot flight from Khabarovsk(KHV) to Petropavlovsk(KHV),Kamchatka. Started shaking violently during climb at 5000m altitude and stomping and rolling. Crew lost control. Cause unknown. All 79 passengers and 7 crew members are killed. c/n 86601103 1st flight : 1958 2 AM-3M engines. Location : ca.10km 48°53'38"N 136°12'15"E , 90km from Khabarovsk. No pictures found of this aircraft.
calculation : *5* (loads)
manoeuvre load : 8.0 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 1.2 [g]
design flight time : 3.08 [hours]
design cycles : 4405 sorties, design hours : 13589 [hours]
operational wing loading : 3637 [N/m^2]
wing stress (3 g) during operation : 232 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.87 ["]
max. angle of attack (stalling angle, clean) : 12.29 ["]
angle of attack at max. speed : 1.43 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.27 [ ]
lift coefficient at max. angle of attack : 1.14 [ ]
max. lift coefficient full flaps : 1.41 [ ]
induced drag coefficient at max.speed : 0.0047 [ ]
drag coefficient at max. speed : 0.0352 [ ]
drag coefficient (zero lift) : 0.0304 [ ]
lift/drag ratio at max. speed : 7.54 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 69290 [kg]): 259 [km/u]
stalling speed at sea-level with full flaps (normal landing weight): 224 [km/u]
landing speed at sea-level (normal landing weight : 63924 [kg]): 258 [km/hr]
max. rate of climb speed : 479 [km/hr] at sea-level
max. endurance speed : 452 [km/u] min. fuel/hr : 5114 [kg/hr] at height : 6706 [m]
max. range speed : 698 [km/u] min. fuel consumption : 8.459 [kg/km] at cruise height : 9449 [m]
OK-NDD op Arlanda airport
On June 1, 1970, the Tu-104A OK-NDD “Plzen” of the CSA crashed during the approach of RW36 from Tripoli(TIP)airport, Libya. The 10 crew members and 3 (!?) passengers are all killed. c/n 96601803 first flight : 1959 2 AM-3M engines. Location : 5.5km south of Tripoli. +-3km 32°50'24"N 13°17'27"E
cruising speed : 840 [km/hr] at 9000 [m] (power:42 [%])
max. operational speed (Mmo) : 970.00 [km/hr] (Mach 0.91 ) at 10700 [m] (power:52.0 [%])
airflow : 335.0 [kg/s]
speed of thrust jet : 1556 [km/hr]
climbing speed at sea-level (loaded) : 1090 [m/min]
climbing speed at 1000 [m] with 1 engine out (PUF / MTOW) : 939 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 324.9 [km/u]
high wheel pressure, can only take off from paved runways
take-off distance at sea-level concrete runway : 1876 [m]
take-off distance at sea-level over 15 [m] height : 1986 [m]
landing run : 1275 [m]
landing run from 15 [m] : 2184 [m]
lift/drag ratio : 11.06 [ ]
max. theoretical ceiling : 18900 [m] with flying weight :69290 [kg] line 3359
climb to 1000m with max payload : 0.97 [min]
climb to 2000m with max payload : 1.90 [min]
On 09 February 1976, the Tu-104A CCCP42327 of the Aeroflot crashed during take-off from Irkutsk (IKT). All 24 passengers are killed. c/n 66600201 first flight : 1956 22069 flight hours 10308 flights. 2 x AM-3M engines.
Location: +-1km 52°16'21.69"N 104°22'25.14"O
climb to 3000m with max payload : 2.77 [min]
climb to 5000 [m] with max payload : 4.35 [min]
minimum flying speed at 11211 [m] : 555 [km/hr]
theoretical ceiling fully loaded (mtow- 60 min. fuel:69290 [kg] ) : 18900 [m]
calculation *10* (action radius & endurance)
published range : 3239 [km] with 6 crew and 11553 [kg] useful load and 88.1 [%] fuel
range : 3178 [km] with 12000.0 [kg] max. useful load (86.5 [%] fuel)
range max. fuel : 3676 [km] with 70 passengers with each 16 [kg] luggage and 1810 [kg] cargo and 100 [%] fuel
range : 3569 [km] with 98 passengers with each 16 [kg] luggage and 97.1 [%] fuel
Available Seat Kilometres (ASK) : 257336 [paskm]
max range theoretically with additional fuel tanks total 44375.0 [litre] fuel : 4197 [km]
useful load with range 500km : 31803 [kg]
useful load with range 500km : 70 passengers
production (theor.max load): 26715 [tonkm/hour]
production (useful load): 10080 [tonkm/hour]
production (passengers): 58800 [paskm/hour]
combi aircraft mail/freight/passengers
oil and fuel consumption per tonkm : 0.236 [kg]
fuel cost per paskm : 0.107 [eur]
crew cost per paskm : 0.013 [eur]
time between engine failure : 962 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
writing off per paskm : 0.040 [eur]
insurance per paskm : 0.0019 [eur]
maintenance cost per paskm : 0.014 [eur]
direct operating cost per paskm : 0.177 [eur]
direct operating cost per tonkm (max. load): 0.389 [eur]
direct operating cost per tonkm (normal useful load): 1.030 [eur]
CCCP-42369 on Copenhagen, 60s.
January 13, 1977, a fire breaks out in engine 1 of the Tu-104A CCCP-42369 of the Aeroflot during a flight from Novosibirsk (OVB) to Alma Ata (ALA). Plane starts to circle at 300m altitude to make up fuel. However, fire reaches the fuel tank on which an explosion follows, causing the crew to lose control. The plane crashed 3.5km from Alma Ata airport, killing all 6 crew members and 90 passengers. c/n 86601203 first flight : 1958, 27189 flight hours, 12819 flights 2x AM-3M engines. Location : ca.1km 43°20'25"N 77°05'49"E
On 07 February 1981, the Tu-104A CCCP-42332 of the Russian Navy crashed at the start from Pushkin aiport (ULLP), 20km south of Leningrad. Comes loose from the ground but at 50m altitude it made a turn to the right after which it dives upside down into the ground. The cause is a wrong distribution of passengers and cargo, the latter also started to shift, after which the
center of gravity was wrong, making the aircraft uncontrollable. c/n 76600402 1 e vl 1957 2xAM-3M engines. All 45 passengers (naval personnel who returned to Vladivostok after an exercise in Leningrad) and 6 crew members are killed. Flight from Pushkin airport to Khabarovsk(KHV) Location : +-500M 59°41'46.62"N 30°21'41.49"E
Cockpit van de Tu-104A OK-LDC
Literature :
wikipedia
Jane’s all the world aircraft 1964-1965 page 328
Alles over Russische vliegtuigen page 230
Praktisch handboek vliegtuigen deel 5 page 168
https://www.baaa-acro.com/aircraft/tupolev-tu-104
Verkehrsflugzeuge page 109
Alles over straalverkeersvliegtuigen page135
www.aviation-safety.net
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