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weight and performance calculations for the Tupolev Tu-124V COOKPOT
***** PRELIMINARY FILE ****
Tupolev Tu-124V COOKPOT
role : short-range jet airliner
importance : ****
first flight : 29 March 1960 from Zhukovsky airfield. operational : Tu-124 : October
1962 route Tallin(Estonia) – Moscow Tu-124V : 1964
country : Russia
NATO reporting name :
design :
production : 164 aircraft, Factory 135 at Kharkiv, Ukraine 1962-1965
general information :
Scaled down Tu-104. Designed as replacement for the Il-14 airliner. It was the first
Russian jetliner that used turbofan engines.
It had double-slotted flaps, a centre-section airbrake and automatic spoilers.
The Tu-124 had a drogue-parachute for emergency landings on short runways and it
had low pressure tires for operating on unpaved runways.
The engines in the wing root gave more vibrations in the fuselage then pylon mounted
or tail mounted engines. The vibrations reduced the fatigue life of the wing.
The Tu-124 had standard seating for 44 passengers. The improved Tu-124V had standard seating for 56 passengers with a higher Take-off weight and better range, entering service in 1964.
primary users : Aeroflot, CSA, Interflug, Iraqi airways
Accommodation:
flight crew : 3 cabin crew : 2
flight crew consist of pilot, co-pilot and flight engineer
passengers : seating for 56 in two class : 6 business class and 50 economy class seats ( 32 -in pitch)
engine : 2 Soloviev D-20P turbofan engines of 49.03 [KN](11022.2 [lbf])
dimensions :
wingspan : 25.55 [m], length : 30.58 [m], height : 8.08 [m]
wing area : 119.48 [m^2]
weights :
operating empty weight : 22500 [kg] max. structural payload : 6000 [kg]
Zero Fuel weight (ZFW) : 28500 [kg] max. landing weight (MLW) : 0 [kg]
max.take-off weight : 36500 [kg] weight fuel : 10496 [kg] (13120 [liter])
performance :
Max. operating Mach number (Mmo) : 0.84 [Mach] (900 [km/hr]) at 10000 [m]
normal cruise speed : 850 [km/hr] (Mach 0.80 ) at 10500 [m] (33 [%] power)
service ceiling : 11700 [m]
range with max fuel : 3342 [km] and allowance for 333.1 [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 double-slotted flaps air foil : Tupolev
sweep angle 3/4 chord: 35.0 [°]
engines in the wing root 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 : O
calculation : *1* (dimensions)
measured wing chord : 4.68 [m] at 50% wingspan
mean wing chord : 4.68 [m]
calculated average wing chord tapered wing with rounded tips: 4.79 [m]
wing aspect ratio : 5.46 []
seize (span*length*height) : 6313 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 49.0 [kg/hr]
fuel consumption (econ. cruise speed) : 2351.7 [kg/hr] (2939.6 [litre/hr]) at 33 [%] power
distance flown for 1 kg fuel : 0.36 [km/kg] at 10500 [m] height, sfc : 73.0 [kg/KN/h]
total fuel capacity : 13120 [litre] (10496 [kg])
calculation : *3* (weight)
weight engine(s) dry : 2936.0 [kg] = 29.94 [kg/KN]
weight 259.7 litre oil tank : 22.08 [kg]
oil tank filled with 0.6 litre oil : 0.6 [kg]
oil in engine 16.4 litre oil : 14.7 [kg]
fuel in engine 12.0 litre fuel : 8.83 [kg]
weight fuel lines 13.1 [kg]
weight engine cowling 294.2 [kg]
total weight propulsion system : 3289 [kg](9.0 [%])
***************************************************************
fuselage aluminium frame : 6065 [kg]
typical cabin layout for 56 passengers : economy : pitch : 81 [cm] ( 2+2 ) seating in 14.5 rows
pax density (normal seating) : 0.90 [m2/pax]
high density seating passengers : 71 at 4 -abreast seating in 17.9 rows, pitch 76 [cm]
weight 1 toilets : 14.5 [kg]
weight 3 hand fire extinguisher : 8 [kg]
weight 1 galleys : 49.3 [kg]
weight overhead stowage for hand luggage : 19.6 [kg]
weight 1 closets : 5.6 [kg]
weight 31 windows : 27.9 [kg]
weight 1 over wing emergency exits : 2.4 [kg]
weight 3 life rafts : 70.0 [kg]
weight oxygen masks & oxygen generators : 36.4 [kg]
weight emergency flare installation : 10 [kg]
weight 2 emergency evacuation slides : 12.2 [kg]
weight 2 entrance/exit doors : 24.0 [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 : 82.75 [m3]
passenger cabin max.width : 2.70 [m] cabin length : 20.70 [m] cabin height : 1.90 [m]
floor area : 50.4 [m2]
pressure difference :0.54 [kg/cm2]
weight rear pressure bulkhead : 88.3 [kg]
weight air pressurization system : 26.5 [kg]
fuselage covering ( 194.7 [m2] duraluminium 2.59 [mm]) : 1327.6 [kg]
weight floor beams : 99.4 [kg]
weight cabin furbishing : 217.8 [kg]
weight cabin floor : 464.1 [kg]
fuselage (sound proof) isolation : 140.7 [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: 24.5 [kg]
weight lighting : 14.0 [kg]
weight electricity generator : 14.0 [kg]
weight controls : 12.4 [kg]
weight seats : 305.0 [kg]
weight 6560 [litre] main central fuel tanks empty : 367.4 [kg]
weight air conditioning : 84 [kg]
total weight fuselage : 9423 [kg](25.8 [%])
***************************************************************
total weight aluminium ribs (399 ribs) : 1302 [kg]
weight engine mounts : 49 [kg]
weight fuel tanks empty for total 6560 [litre] fuel : 367 [kg]
Initial Tu-124 had seating for 44 passengers, this was raised to 56 passenger in the Tu-124V variant.
weight wing covering (painted aluminium 2.94 [mm]) : 1896 [kg]
total weight aluminium spars (multi-cellular wing structure) : 1933 [kg]
weight wings : 5131 [kg]
weight wing/square meter : 42.95 [kg]
weight rubber de-icing boots : 28.1 [kg]
weight fin & rudder (7.6 [m2]) : 326.6 [kg]
weight stabilizer & elevator (13.4 [m2]): 578.2 [kg]
weight fowler flaps (7.4 [m2]) : 164.4 [kg]
total weight wing surfaces & bracing : 6645 [kg] (18.2 [%])
*******************************************************************
Can also operate from unpaved runways
wheel pressure : 4015.0 [kg]
weight 8 Dunlop main wheels (1130 [mm] by 226 [mm]) : 668.8 [kg]
weight 2 Dunlop nose wheels : 83.6 [kg]
weight hydraulic wheel-brakes : 28.5 [kg]
weight pneumatic-hydraulic shock absorbers : 38.0 [kg]
weight wheel hydraulic operated retraction system : 476.2 [kg]
weight undercarriage struts with axle 1062.0 [kg]
total weight landing gear : 2357.0 [kg] (6.5 [%]
*******************************************************************
********************************************************************
calculated empty weight : 21715 [kg](59.5 [%])
weight oil for 4.7 hours flying : 231.3 [kg]
weight catering : 88.1 [kg]
weight water : 35.2 [kg]
weight crew : 405 [kg]
weight crew lugage,nav.chards,flight doc.,miscell.items : 26 [kg]
operational weight empty : 22500 [kg] (61.6 [%])
********************************************************************
weight 56 passengers : 4312 [kg]
weight luggage : 896 [kg]
weight cargo : 792 [kg]
zero fuel weight (ZFW): 28500 [kg](78.1 [%])
weight fuel for landing (1.0 hours flying) : 2352 [kg]
max. landing weight (MLW): 30852 [kg](84.5 [%])
max. fuel weight : 32996 [kg] (90.4 [%])
payload with max fuel : 38 passengers+luggage 3504 [kg]
published maximum take-off weight : 36500 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 372 [kg/KN]
power loading (operational without useful load) : 343 [kg/kN]
power loading (Take-off) 1 PUF: 744 [kg/KN]
max. total take-off power : 98.1 [KN]
calculation : *5* (loads)
manoeuvre load : 8.6 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 1.8 [g]
design flight time : 3.15 [hours]
design cycles : 10920 sorties, design hours : 34349 [hours]
operational wing loading : 2762 [N/m^2]
wing stress (3 g) during operation : 193 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.97 ["]
max. angle of attack (stalling angle, clean) : 12.63 ["]
angle of attack at max. speed : 0.85 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.21 [ ]
lift coefficient at max. angle of attack : 1.11 [ ]
max. lift coefficient full flaps : 1.38 [ ]
induced drag coefficient at max.speed : 0.0037 [ ]
drag coefficient at max. speed : 0.0236 [ ]
drag coefficient (zero lift) : 0.0200 [ ]
lift/drag ratio at max. speed : 9.08 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 34148 [kg]): 231 [km/u]
stalling speed at sea-level with full flaps (normal landing weight): 197 [km/u]
landing speed at sea-level (normal landing weight : 30790 [kg]): 226 [km/hr]
max. rate of climb speed : 552 [km/hr] at sea-level
max. endurance speed : 429 [km/u] min. fuel/hr : 1783 [kg/hr] at height : 5182 [m]
max. range speed : 735 [km/u] min. fuel consumption : 2.8[kg/km] at cruise height :
9754 [m]
cruising speed : 850 [km/hr] at 10500 [m] (power:31 [%])
max. operational speed (Mmo) : 900.00 [km/hr] (Mach 0.84 ) at 10000 [m] (power:36.8
[%])
airflow : 120.4 [kg/s]
speed of thrust jet : 1813 [km/hr]
climbing speed at sea-level (loaded) : 1635 [m/min]
climbing speed at 1000 [m] with 1 engine out (PUF / MTOW) : 1455 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 286.8 [km/u]
take-off distance at sea-level gras field : 1478 [m]
take-off distance at sea-level over 15 [m] height : 1563 [m]
landing run : 982 [m]
landing run from 15 [m] : 1782 [m]
lift/drag ratio : 12.55 [ ]
max. theoretical ceiling : 19200 [m] with flying weight :34148 [kg] line 3359
climb to 1000m with max payload : 0.64 [min]
climb to 2000m with max payload : 1.25 [min]
climb to 3000m with max payload : 1.83 [min]
climb to 5000 [m] with max payload : 2.87 [min]
CSA sold its remaining Tu-124’s to Iraqi Airways in 1973. They were destroyed during the Gulf War, early 1990 .
minimum flying speed at 11700 [m] : 510 [km/hr]
theoretical ceiling fully loaded (mtow- 60 min. fuel:34148 [kg] ) : 19200 [m]
calculation *10* (action radius & endurance)
published range : 3342 [km] with 5 crew and 4754 [kg] useful load and 88.1 [%] fuel
range : 2892 [km] with 6000.0 [kg] max. useful load (76.2 [%] fuel)
range : 3178 [km] with 56.0 passengers with each 16 [kg] luggage and 83.8 [%] fuel
range max. fuel : 3794 [km] with 3504.0 [kg] useful load and 100.0 [%] fuel
Available Seat Kilometres (ASK) : 177957 [paskm]
max range theoretically with additional fuel tanks total 17500.0 [litre] fuel : 5000 [km]
useful load with range 500km : 12617 [kg]
useful load with range 500km : 56 passengers
production (theor.max load): 10724 [tonkm/hour]
production (useful load): 5100 [tonkm/hour]
production (passengers): 47600 [paskm/hour]
combi aircraft mail/freight/passengers
oil and fuel consumption per tonkm : 0.224 [kg]
fuel cost per paskm : 0.050 [eur]
crew cost per paskm : 0.013 [eur]
economic hours : 22300 [hours] is less then design hours
time between engine failure : 1068 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
writing off per paskm : 0.017 [eur]
insurance per paskm : 0.0012 [eur]
maintenance cost per paskm : 0.008 [eur]
direct operating cost per paskm : 0.089 [eur]
direct operating cost per tonkm (max. load): 0.397 [eur]
direct operating cost per tonkm (normal useful load): 0.835 [eur]
Literature :
Jane’s commercial transport aircraft page 233
Verkehrsflugzeuge page 109
Verkeersvliegtuigen Moussault page 67, 138
praktisch handboek vliegtuigen deel 5
jane’s all the world aircraft 1964-1965 page 329
nl.wikepedia.org
samdimdesign.free.fr/HTML/Tu124/tu124.html
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 27 June 2022 contact : info.aircraftinvestigation@gmail.com python 3.7.4