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weight and performance calculations for the Tupolew Tu-154A
***** PRELIMINARY FILE ****
Balkan Bulgarian Tu-154B LZ-BTD c/n 74A058 at Schiphol airport. Built as Tu-154A, later it was converted into a Tu-154B.
Tupolew Tu-154A
role : jet airliner
importance : ****
first flight : end of 1973 operational : April 1974
country : Russia
NATO reporting name : CARELESS
design :
production : 47 aircraft
general information :
New version of the Tu-154 with improved wing, controls and valves and with greater power.
It was introduced in 1974. By 1975, 110 Tu-154s had been delivered to the Aeroflot.
MSRP-12 radar. Measured chord at root : 8.85m at tip : 2.24m
primary users : Aeroflot, Malev, Egyptair
Accommodation:
flight crew : 4 cabin crew : 5
flight crew consist of pilot, co-pilot, navigator and flight engineer
passengers : seating for 146 in two class : 14 first class and 132 economy class seats
( 32 -in pitch) exit limit : 168 passengers
engine : 3 Kuznetsov NK-8-2U turbofan engines of 103.0 [KN] (23154.9 [lbf])
dimensions :
wingspan : 37.55 [m], length : 47.9 [m], height : 11.4 [m]
wing area : 201.45 [m^2] fuselage exterior width : 3.8 [m]
weights :
operating empty weight : 45500 [kg] max. structural payload : 18000 [kg]
Zero Fuel weight (ZFW) : 63500 [kg] max. landing weight (MLW) : 78000 [kg]
max.take-off weight : 94000 [kg] weight fuel : 39602 [kg] (49502 [liter])
performance :
Max. operating Mach number (Mmo) : 0.88 [Mach] (956 [km/hr]) at 9500 [m]
normal cruise speed : 923 [km/hr] (Mach 0.86 ) at 10000 [m] (27 [%] power)
economic cruise speed : 900 [km/hr] (Mach 0.84 ) at 10000 [m]
service ceiling : 11000 [m]
range with max fuel : 5300 [km] (ATA domestic fuel reserves - 820.0 [km] alternate)
description :
low-wing cantilever monoplane with retractable landing gear with nose wheel
Wings : all-metall three-spar fail-safe wing structure
with triple slotted flaps with full-span slotted LE flaps (slats) airfoil : Tupolev
sweep angle 3/4 chord: 35.0 [°]
engines attached to the tail, landing gear attached to the wings, fuel tanks in the wings
Fuselage : Pressurized conventional all-metal semi-monocoque fail safe structure of circular section
calculation : *1* (dimensions)
measured wing chord : 8.85 [m] at root
mean wing chord : 5.36 [m]
calculated average wing chord tapered wing with rounded tips: 5.41 [m]
wing aspect ratio : 7.00 []
seize (span*length*height) : 20505 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 9.3 [kg/hr]
fuel consumption (econ. cruise speed) : 5823.8 [kg/hr] (7279.7 [litre/hr]) at 25 [%] power
distance flown for 1 kg fuel : 0.15 [km/kg] at 10000 [m] height, sfc : 76.0 [kg/KN/h]
total fuel capacity : 49502 [litre] (39602 [kg])
Balkan Bulgarian LZ-BTD landing at Schiphol
calculation : *3* (weight)
weight engine(s) dry : 6750.0 [kg] = 21.84 [kg/KN]
weight 91 litre oil tank : 7.74 [kg]
oil tank filled with 1.9 litre oil : 1.7 [kg]
oil in engine 3.8 litre oil : 3.4 [kg]
fuel in engine 16.9 litre fuel : 12.36 [kg]
weight fuel lines 80.4 [kg]
weight engine cowling 803.4 [kg]
weight thrust reversers 463.5 [kg]
total weight propulsion system : 8123 [kg](8.6 [%])
***************************************************************
Accommodation cabin facilities:
typical 2-class cabin layout for 146 passengers : economy : pitch : 81.3 [cm] 32.0 [-in]
( 3+3 ) seating in 25.5 rows
weight seats : 775.0 [kg]
high density seating passengers : 167 [pax] at 6 -abreast seating in 27.9 rows, pitch 75 [cm] 29.5 [-in]
pax density, normal seating : 0.63 [m2/pax], high density seating : 0.55 [m2/pax]
weight 3 lavatories : 49.4 [kg]
weight 1 galleys : 108.7 [kg]
weight overhead stowage for hand luggage : 51.1 [kg]
weight 3 wardrobe closets : 29.2 [kg]
weight 53 windows : 47.7 [kg]
weight 4 1.83x0.80 [m] entrance/exit doors : 199.2 [kg]
weight 2 (135x120 cm) freight doors (belly) : 100.4 [kg]
total belly baggage/cargo hold volume : 34.84 [m3]
passenger compartment volume : 109 [m3]
passenger cabin max.width : 3.58 [m] cabin length : 26.74 [m] cabin height : 2.02 [m]
floor area : 91.9 [m2]
weight cabin facilities : 1360.7 [kg]
safety facilities:
weight 4 over wing emergency exits (90x48 cm): 94.9 [kg]
weight 7 hand fire extinguisher : 22 [kg]
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators : 94.9 [kg]
weight emergency flare installation : 10 [kg]
weight 4 emergency evacuation slides : 126.1 [kg]
weight safety equipment & facilities : 463 [kg]
fuselage construction:
fuselage aluminium frame : 10453 [kg]
floor loading (payload/m2): 196 [kg/m2]
weight rear pressure bulkhead : 174.2 [kg]
Tu-154A flying over the Volga river. CCCP-85070 was delivered in 1974 to Aeroflot as Tu-154A. It was converted to Tu-154B around 1981 and given new registration RA-85070. It was withdrawn from service in 1998 and scrapped.
fuselage covering ( 330.4 [m2] duraluminium 2.91 [mm]) : 2526.5 [kg]
weight floor beams : 549.2 [kg]
weight cabin furbishing : 747.3 [kg]
weight cabin floor : 1395.1 [kg]
fuselage (sound proof) isolation : 238.8 [kg]
weight empty 164 [litre] potable water tank : 14.5 [kg]
weight empty waste tank : 14.6 [kg]
weight engine mounts : 154 [kg]
weight fuselage structure : 16267.7 [kg]
Avionics:
weight HF and UHF radio : 7.0 [kg]
weight dual cloud-collision MSRP-12 radar : 25.0 [kg]
weight VOR/ILS,RMI,Doppler,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 : 9 [kg]
weight avionics : 83.0 [kg]
Systems:
Air-conditioning and pressurization system maintains sea level conditions up to 7100 [m]
and gives equivalent of 2100 [m] at 12500 [m]. pressure differential : 0.62 [bars] (kg/cm2)
pressurized fuselage volume : 430 [m3]
Aeroflot Tu-154A CCCP-85086 c/n 74A086 at Paris (CDG), April 1979
weight air-conditioning and pressurization system : 222 [kg]
weight APU / engine starter: 51.5 [kg]
weight lighting : 48.2 [kg]
weight engine-driven 40kVA electricity generators : 36.5 [kg]
weight controls : 19.5 [kg]
weight systems : 377.7 [kg]
total weight fuselage : 18552 [kg](19.7 [%])
***************************************************************
total weight aluminium ribs (895 ribs) : 3352 [kg]
weight 7 fuel tanks empty for total 49502 [litre] fuel : 2772 [kg]
weight wing covering (painted aluminium 2.13 [mm]) : 2322 [kg]
total weight aluminium spars (multi-cellular wing structure) : 2305 [kg]
weight wings : 7980 [kg]
weight wing/square meter : 39.61 [kg]
weight thermal leading-edge anti-icing : 41.3 [kg]
weight ailerons (4.0 [m2]) : 80.3 [kg]
weight fin (19.6 [m2]) : 780.9 [kg]
weight rudder (7.9 [m2]) : 151.4 [kg]
weight tailplane (stabilizer) (52.4 [m2]): 1457.8 [kg]
weight elevators (17.5 [m2]): 188.4 [kg]
weight flight control hydraulic servo actuators: 52.1 [kg]
weight triple slotted flaps (31.7 [m2]) : 538.9 [kg]
weight leading edge slats (18.5 [m2]) : 204.8 [kg]
total weight wing surfaces & bracing : 14248 [kg] (15.2 [%])
*******************************************************************
tire pressure main wheels : 7.86 [Bar] (nitrogen), ply rating : 20 PR
tire speed limit : 364 [km/hr]
footprinttyre : 0.025 [m2] total footprint : 0.32 [m2]
downforce : 2851.2 [KN/m2] ACN2 : 24 [ ]
Aircraft Classification Number, MTOW on rigid runway and medium subgrade strength (B) : 25 [ ]
Can also operate from unpaved runways subgrade B
wheel pressure : 6893.3 [kg]
weight 12 main wheels (930 [mm] by 305 [mm]) : 545.0 [kg]
weight 2 nose wheels : 45.4 [kg]
weight multi-disc wheel-brakes : 63.5 [kg]
weight flywheel detector type anti-skid units : 12.6 [kg]
weight oleo-pneumatic shock absorbers : 84.7 [kg]
weight wheel hydraulic operated retraction system : 655.1 [kg]
weight undercarriage struts (six-wheel bogies) with axle 1836.5 [kg]
total weight landing gear : 3242.7 [kg] (3.4 [%]
*******************************************************************
********************************************************************
calculated empty weight : 44165 [kg](47.0 [%])
weight oil for 6.9 hours flying : 75.9 [kg]
weight lifejackets : 65.7 [kg]
weight 3 life rafts : 91.2 [kg]
weight catering : 181.2 [kg]
weight water : 144.9 [kg]
weight crew : 729 [kg]
weight crew lugage,nav.chards,flight doc.,miscell.items : 47 [kg]
operational weight empty : 45500 [kg] (48.4 [%])
********************************************************************
weight 146 passengers : 11242 [kg]
weight luggage : 2336 [kg]
weight cargo : 4422 [kg] (cargo+luggage/m3 belly : 177 [kg/m3])
zero fuel weight (ZFW): 63500 [kg](67.6 [%])
weight fuel for landing (2.5 hours flying) : 14500 [kg]
max. landing weight (MLW): 78000 [kg](83.0 [%])
max. fuel weight : 85102 [kg] (90.5 [%])
payload with max fuel : 96 passengers+luggage 8898 [kg]
published maximum take-off weight : 94000 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 304 [kg/KN]
power loading (Take-off) 1 PUF: 456 [kg/KN]
max. total take-off power : 309.0 [KN]
calculation : *5* (loads)
manoeuvre load : 8.6 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 0.9 [g]
design flight time : 2.48 [hours]
design cycles : 18119 sorties, design hours : 44972 [hours]
max. wing loading (MTOW & flaps retracted) : 467 [kg/m2]
wing stress (2 g) during operation : 211 [N/kg] at 2g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.57 ["]
max. angle of attack (stalling angle, clean) : 14.00 ["]
max. angle of attack (full flaps) : 18.20 ["]
angle of attack at max. speed : 1.70 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.13 [ ]
lift coefficient at max. speed : 0.27 [ ]
lift coefficient at max. angle of attack : 1.29 [ ]
max. lift coefficient full flaps : 2.27 [ ]
drag coefficient at max. speed : 0.0292 [ ]
drag coefficient at econ. cruise speed : 0.0295 [ ]
induced drag coefficient at econ. cruise speed : 0.0048 [ ]
drag coefficient (zero lift) : 0.0247 [ ]
lift/drag ratio at max. speed : 9.27 [ ]
calculation : *8* (speeds
take-off safety speed (V2) : 233 [km/u]
take-off (initial climb) speed (Vto) : 284 [km/u]
stalling speed clean at sea-level (OW loaded : 88176 [kg]): 266 [km/u]
max. rate of climb speed : 552 [km/hr] at sea-level
max. endurance speed (Vbe): 545 [km/u] min. fuel/hr : 4284 [kg/hr] at height : 8534 [m]
max. range speed (Vbr): 802 [km/u] min. fuel consumption : 6.165 [kg/km] at cruise height : 10363 [m]
cruising speed : 923 [km/hr] at 10000 [m] (power:26 [%])
max. operational speed (Mmo) : 956.00 [km/hr] (Mach 0.88 ) at 9500 [m] (power:28.3 [%])
airflow at cruise speed per engine : 172.8 [kg/s]
speed of thrust jet : 1474 [km/hr]
initial descent speed 10000 - 7315 [m]: Mach 0.75
descent speed 7315 - 3048 [m]: 537 [km/u]
approach speed 3048 - 500 [m] (clean): 463 [km/u]
stalling speed clean at 500 [m] height at Max.Landing Weight : 78000 [kg]): 256 [km/u]
final approach speed at sea-level with full flaps (normal landing weight) (Vapp): 219 [km/u]
ICAO Aircraft Approach Category (APC) : B
landing speed at sea-level (normal landing weight(Vtd): 77837 [kg]): 194 [km/hr]
stalling speed at sea-level with full flaps (max. landing weight): 168 [km/u]
rate of climb at sea-level ROC (loaded) : 1246 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF / MTOW) : 1158 [m/min]
rate of descent: 457 [m/min]
calculation : *9* (regarding various performances)
low wheel pressure, can also take off from unpaved runways
take-off distance at sea-level concrete runway : 1119 [m]
take-off distance at sea-level gravel/packed earth field : 1418 [m]
take-off distance at sea-level over 15 [m] height : 1230 [m]
balanced runway length at MTOW and at SL (FAR) : 2149 [m]
landing run (MLW) : 756 [m]
landing run (C.A.R.) from 15 [m] at SL, dry runway : 1202 [m]
landing run (C.A.R.) from 15 [m] at SL, wet runway : 1502 [m]
lift/drag ratio : 12.91 [ ]
climb to 5000 [m] with max payload : 3.71 [min]
climb to 10000 [m] with max payload : 11.43 [min]
descent time from 10000 [m] to 250 [m] : 24.33 [min]
ceiling limited by max. pressure differential 16175 [m]
theoretical ceiling fully loaded (mtow- 60 min.fuel: 88176 [kg] ) : 17400 [m]
calculation *10* (action radius & endurance)
range with max. payload: 4619 [km] with 18000.0 [kg] max. useful load (77.0 [%] fuel)*
range with high density pax: 5013 [km] with 167 passengers (83.1 [%] fuel)*
range with typical two-class pax: 5342 [km] with 146 passengers (88.2 [%] fuel)*
range with max.fuel : 6120 [km] with 9 crew and 96 passengers and 100.0 [%] fuel*
ferry range : 6369 [km] with 4 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 61538.9 [litre] fuel : 7765 [km] *
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 808687 [paskm]
useful load with range 1000km : 18000 [kg]
useful load with range 1000km : 167 passengers
production (theor.max load): 16614 [tonkm/hour]
production (useful load): 16614 [tonkm/hour]
production (passengers): 143744 [paskm/hour]
oil and fuel consumption per tonkm : 0.351 [kg]
fuel cost per paskm : 0.041 [eur]
crew cost per paskm : 0.008 [eur]
list price 2023 : 117 [mln USD]
economic hours : 44600 [hours] is 1 [%] less then design hours
time between engine failure : 1220 [hr]
writing off per paskm : 0.015 [eur]
insurance per paskm : 0.0014 [eur]
maintenance cost per paskm : 0.019 [eur]
direct operating cost per paskm : 0.085 [eur]
direct operating cost per tonkm (max. load): 0.736 [eur]
direct operating cost per tonkm (normal useful load): 0.736 [eur]
accidents with fatalities > see the accident file
Literature :
https://en.wikipedia.org/wiki/Tupolev_Tu-154
https://contentzone.eurocontrol.int/aircraftperformance/details.aspx?ICAO=T154
Air international june’97 page 35
Bekende vliegtuigeb van Italie & Rusland page 134
The flier’s handbook page 120
Jane’s all the world aircraft 1979-’80 page 217
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 22 October 2022 contact : info.aircraftinvestigation@gmail.com python 3.7.4