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weight and performance calculations for the Tupolev Tu-134
***** PRELIMINARY FILE ****
Tupolev Tu-134
importance : ****
first flight : 29 July 1963 operational : November 1966
country : Russia
NATO reporting name : CRUSTY
production : Tu-134 : 100 aircraft , all versions : Tu-134(A,B) 854
general information :
Designed to close the gap between the Tu-124 and the IL-62. It was intended for the medium distance. It was just like the Caravelle equipped with 2 engines at the tail. The first scheduled service took place in September 1967 between Moscow and Sotschi.
primary users : Aeroflot, CSA, LOT, Malev
flight crew : 3 cabin crew : 3 passengers : 72
flight crew consist of pilot, co-pilot and radio operator
engine : 2 Soloviev D-30 turbofan engines of 66.69 [KN](14992.3 [lbf])
dimensions :
wingspan : 29.0 [m], length : 34.35 [m], height : 9.02 [m]
wing area : 127.3 [m^2]
weights :
operating empty weight : 27500 [kg] max. structural payload : 7700 [kg]
Zero Fuel weight (ZFW) : 35200 [kg] max. landing weight (MLW) : 40000 [kg]
max.take-off weight : 44500 [kg]
performance :
Max. operating Mach number (Mmo) : 0.90 [Mach] ( Mmo Mach 1000 [km/hr]) op 7500 [m]
normal cruise speed : 870 [km/hr] (Mach 0.82 ) op 11000 [m] (29 [%] power)
service ceiling : 12000 [m]
range with max fuel : 2500 [km] and allowance for 216.7 [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 : root: PR-1-10S-9 (15.7%); tip: PR-1-10S-9 (12%)
sweep angle 3/4 chord: 35.0 [°]
engines attached to the tail, landing gear attached to the wings, fueltanks in the wings
construction : all-metal aluminium-alloy stressed-skin construction with pressurized
fuselage. fuselage shape : 0
Tu-134A-3
calculation : *1* (dimensions)
measured wing chord : 4.39 [m] at 50% wingspan
mean wing chord : 4.39 [m]
calculated average wing chord tapered wing with rounded tips: 4.41 [m]
wing aspect ratio : 6.61 []
seize (span*length*height) : 8985 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 66.7 [kg/hr]
fuel consumption (econ. cruise speed) : 2482.2 [kg/hr] (3102.8 [litre/hr]) at 29 [%] power
distance flown for 1 kg fuel : 0.35 [km/kg] at 11000 [m] height, sfc : 63.2 [kg/KN/h]
estimated total fuel capacity : 10120 [litre] (8096 [kg])
calculation : *3* (weight)
weight engine(s) dry : 2800.0 [kg] = 20.99 [kg/KW]
weight 259.0 litre oil tank : 22.01 [kg]
oil tank filled with 0.8 litre oil : 0.8 [kg]
oil in engine 22.3 litre oil : 20.0 [kg]
fuel in engine 16.4 litre fuel : 12.00 [kg]
weight fuel lines 10.1 [kg]
weight engine cowling 400.1 [kg]
total weight propulsion system : 3265 [kg](7.3 [%])
***************************************************************
fuselage aluminium frame : 7684 [kg]
typical cabin layout for 72 passengers : average pitch : 81 [cm] ( 2+2 ) seating in 18.0 rows
pax density (normal seating) : 0.92 [m2/pax]
high density seating passengers : 92 at 5 -abreast seating in 18.3 rows, pitch 75 [cm]
weight 2 toilets : 19.0 [kg]
weight 4 hand fire extinguisher : 11 [kg]
weight pantry : 33.1 [kg]
weight 38 windows : 34.2 [kg]
weight 2 emergency exits : 6.0 [kg]
weight 4 life rafts : 90.0 [kg]
weight oxygen masks & oxygen generators : 46.8 [kg]
weight emergency flare installation : 10 [kg]
weight emergency evacuation slide : 15 [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]
extra main deck space for freight/mail/luggage etc. : 9.75 [m3]
cabin volume (usable), excluding flight deck : 135.56 [m3]
passenger cabin max.width : 2.90 [m] cabin length : 22.96 [m] cabin height : 2.18 [m]
pressure at cruise height 12192.00 [m] : 0.19 [kg/cm2] cabin pressure : 0.77 [kg/cm2]
weight rear pressure bulkhead : 120.0 [kg]
weight air pressurization system : 36.3 [kg]
fuselage covering ( 225.0 [m2] duraluminium 3.06 [mm]) : 1804.8 [kg]
weight floor beams : 130.4 [kg]
weight cabin furbishing : 355.9 [kg]
weight cabin floor : 671.8 [kg]
fuselage (sound proof) isolation : 162.4 [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: 33.3 [kg]
weight lighting : 18.0 [kg]
weight electricity generator : 18.0 [kg]
weight controls : 13.8 [kg]
weight seats : 390.0 [kg]
weight air conditioning : 108 [kg]
weight engine mounts : 67 [kg]
total weight fuselage : 11777 [kg](26.5 [%])
***************************************************************
total weight aluminium ribs (518 ribs) : 1587 [kg]
weight fuel tanks empty for total 10120 [litre] fuel : 567 [kg]
weight wing covering (painted aluminium 3.37 [mm]) : 2319 [kg]
total weight aluminium spars (multi-cellular wing structure) : 2629 [kg]
weight wings : 6536 [kg]
weight wing/square meter : 51.34 [kg]
weight rubber de-icing boots : 31.9 [kg]
weight fin & rudder (9.8 [m2]) : 502.6 [kg]
weight stabilizer & elevator (14.3 [m2]): 736.2 [kg]
weight flight control hydraulic servo actuators: 33.5 [kg]
weight fowler flaps (7.9 [m2]) : 207.7 [kg]
total weight wing surfaces & bracing : 8614 [kg] (19.4 [%])
*******************************************************************
Interflug Tu-134 18 rows x 2+2 seating = 72 pax
wheel pressure : 4895.0 [kg]
weight 8 main wheels (1130 [mm] by 226 [mm]) : 856.8 [kg]
weight 2 nose wheels : 107.1 [kg]
weight hydraulic wheel-brakes : 35.2 [kg]
weight pneumatic-hydraulic shock absorbers : 46.9 [kg]
weight wheel hydraulic operated retraction system : 602.1 [kg]
weight undercarriage struts with axle 1332.2 [kg]
total weight landing gear : 2980.2 [kg] (6.7 [%]
*******************************************************************
********************************************************************
calculated empty weight : 26636 [kg](59.9 [%])
weight oil for 3.4 hours flying : 230.0 [kg]
weight catering : 82.8 [kg]
weight water : 33.1 [kg]
weight crew : 486 [kg]
weight crew lugage,nav.chards,flight doc.,miscell.items : 32 [kg]
operational weight empty : 27500 [kg] (61.8 [%])
********************************************************************
weight 72 passengers : 5544 [kg]
weight luggage : 878 [kg]
weight cargo : 1278 [kg]
zero fuel weight (ZFW): 35200 [kg](79.1 [%])
weight fuel for landing (1.9 hours flying) : 4800 [kg]
max. landing weight (MLW) : 40000 [kg](89.9 [%])
max. fuel weight : 35596 [kg] (80.0 [%])
payload with max fuel : 100 passengers+luggage 8904 [kg]
operational weight with max payload and fuel : 44500 [kg] with fuel tank filled for 61 [%]
published maximum take-off weight : 44500 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 334 [kg/KN]
power loading (operational without useful load) : 317 [kg/kN]
power loading (Take-off) 1 PUF: 667 [kg/KN]
max. total take-off power : 133.4 [KN]
calculation : *5* (loads)
manoeuvre load : 9.5 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 1.8 [g]
design flight time : 2.30 [hours]
design cycles : 13658 sorties, design hours : 31397 [hours]
operational wing loading : 3253 [N/m^2]
wing stress (3 g) during operation : 190 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.85 ["]
max. angle of attack (stalling angle, clean) : 12.19 ["]
angle of attack at max. speed : 0.02 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.15 [ ]
lift coefficient at max. angle of attack : 1.14 [ ]
max. lift coefficient full flaps : 1.41 [ ]
induced drag coefficient at max.speed : 0.0015 [ ]
drag coefficient at max. speed : 0.0191 [ ]
drag coefficient (zero lift) : 0.0176 [ ]
lift/drag ratio at max. speed : 7.95 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 42018 [kg]): 245 [km/u]
stalling speed at sea-level with full flaps (normal landing weight): 215 [km/u]
landing speed at sea-level (normal landing weight : 39942 [kg]): 247 [km/hr]
max. rate of climb speed : 659 [km/hr] at sea-level
max. endurance speed : 495 [km/u] min. fuel/hr : 1689 [kg/hr] at height : 6401 [m]
max. range speed : 809 [km/u] min. fuel consumption : 2.412 [kg/km] at cruise height :
10058 [m]
cruising speed : 870 [km/hr] at 11000 [m] (power:21 [%])
max. operational speed (Mmo) : 1000.00 [km/hr] (Mach 0.90 ) at 7500 [m] (power:38.9 [%])
airflow : 114.4 [kg/s]
speed of thrust jet : 2106 [km/hr]
climbing speed at sea-level (loaded) : 2205 [m/min]
climbing speed at 1000 [m] with 1 engine out (PUF / MTOW) : 2059 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 302.5 [km/u]
high wheel pressure, can only take off from paved runways
take-off distance at sea-level concrete runway : 1117 [m]
take-off distance at sea-level over 15 [m] height : 1192 [m]
landing run : 1194 [m]
landing run from 15 [m] : 2066 [m]
lift/drag ratio : 14.85 [ ]
max. theoretical ceiling : 19300 [m] with flying weight :42018 [kg] line 3359
climb to 1000m with max payload : 0.46 [min]
climb to 2000m with max payload : 0.89 [min]
climb to 3000m with max payload : 1.31 [min]
climb to 5000 [m] with max payload : 2.05 [min]
minimum flying speed at 12000 [m] : 552 [km/hr]
theoretical ceiling fully loaded (mtow- 60 min. fuel:42018 [kg] ) : 19300 [m]
calculation *10* (action radius & endurance)
published range : 2500 [km] with 7700 [kg] useful load and 2167 [kg] fuel reserve 96.2 [%]
fuel
range : 3260 [km] with 6 crew and 7700.0 [kg] useful load and 125.4 [%] fuel
range max. fuel : 2600 [km] with 72 passengers with each 12.2 [kg] luggage and 3160 [kg]
cargo and 100 [%] fuel
range : 3093 [km] with 92 passengers with each 12.2 [kg] luggage and 118.9 [%] fuel
Available Seat Kilometres (ASK) : 187196 [paskm]
max range theoretically with additional fuel tanks total 21250.0 [litre] fuel : 7050 [km]
useful load with range 500km : 15573 [kg]
useful load with range 500km : 72 passengers
production (theor.max load): 13549 [tonkm/hour]
production (useful load): 6699 [tonkm/hour]
production (passengers): 62640 [paskm/hour]
combi aircraft mail/freight/passengers
oil and fuel consumption per tonkm : 0.188 [kg]
fuel cost per paskm : 0.041 [eur]
crew cost per paskm : 0.012 [eur]
economic hours : 22300 [hours] is less then design hours
time between engine failure : 1220 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
writing off per paskm : 0.016 [eur]
insurance per paskm : 0.0013 [eur]
maintenance cost per paskm : 0.015 [eur]
direct operating cost per paskm : 0.085 [eur]
direct operating cost per tonkm (max. load): 0.392 [eur]
direct operating cost per tonkm (normal useful load): 0.793 [eur]
Literature :
Verkeersvliegtuigen page 74
Verkehrsflugzuege page 115
Jane’s commercial transport aircraft page 235
Jane’s all the world aircraft 1979 page 214
The flier’s handbook page 120
Air International jan’96 page 36
Air International feb’00 page 210 Tupolev Tu-134 - Wikipedia
http://www.aircraftmonitor.com/uploads/1/5/9/9/15993320/aircraft_payload_range_analysis_for_financiers___v2.pdf
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