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weight and performance calculations for the Tupolev Tu-124V COOKPOT
Aeroflot Tu-124V CCCP-45054 c/n 4351304 .
Tupolev Tu-124V COOKPOT
role : short-range regional jet airliner
importance : ****
first flight : 29 March 1960 from Zhukovsky airfield. operational : Tu-124V June
1964
country : Russia
NATO reporting name : COOKPOT
production : 139 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 intended mainly for emergency use after engine
failure at take-off but also for emergency landings on short runways.
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 (3 : OK-TEA, OK-TEB, OK-UEC), Interflug (3 : DM-
SDA, DM-SBD, plus ??), Iraqi airways (YI-AEL, YI-AEY)
Accommodation :
flight crew : 3 cabin crew : 1
flight crew consist of pilot, co-pilot and navigator
passengers : seating for 56 in all- coach class seats ( 34 -in pitch)
engine : 2 Soloviev D-20P turbofan engines of 52.9 [KN] (11892 [lbf])
CSA Tu-124V OK-TEB c/n 4 35 15 04 “Centrotex” taken into service November 1964 .
dimensions :
wingspan : 25.55 [m], length overall: 30.58 [m], length of fuselage : 29.31 [m] height :
8.08 [m] wing area gross : 119.48 [m^2] fuselage exterior width : 2.9 [m]
weights :
operating empty weight : 22500 [kg] max. structural payload : 6000 [kg]
Zero Fuel weight (ZFW) : 28500 [kg] max. landing weight (MLW) : 35000 [kg]
max. take-off weight : 38000 [kg] weight usable fuel : 10598 [kg] (13500 [litres])
performance :
Max. operating Mach number (Mmo) : 0.871 [Mach] (970 [km/hr]) at 7500 [m]
critical Mach speed : 0.88 [Mach]
max. cruising speed : 870 [km/hr] (Mach 0.809 ) at 10000 [m] (32 [%] power)
economic cruising speed : 800 [km/hr] (Mach 0.74 ) at 10000 [m]
service ceiling : 11700 [m]
range with max fuel and MTOW : 2100 [km] (ATA domestic fuel reserves - 370.0 [km]
alternate)
description :
*Cantilever low-wing monoplane with retractable landing gear with nose wheel
engines in the wingroot and landing gear attached to the wings, fuel tanks in the
wings and fuselage
*Wings : all-metal two-spar wing structure with double slotted trailing edge flaps with
no leading edge flaps ,with spoilers that can also be used as airbrakes airfoil : Tupolev
average thickness/chord ratio : 12.0 [%], sweep angle 3/4 chord: 35.0 [°]
incidence at root : 3.00 [°], dihedral : -1.0 [°]
*Tail Unit: Cantilever all-metall structure with tailplane attached to the fuselage.
Variable-incidence tailplane
*Fuselage : Pressurized conventional all-metal semi-monocoque fail safe structure of
circular section
calculation : *1* (dimensions) :
measured wing chord at root: 4.68 [m]
measured wing chord at tip : 2.25 [m]
measured geometric tail-angle : 10.0 [° ]
taper ratio : 0.481 [ ]
mean wing chord : 4.68 [m]
wing aspect ratio : 5.46 []
Oswald factor (e): 0.652 []
seize (span*length*height) : 6313 [m^3]
CSA Tu-124V
calculation : *2* (fuel consumption) :
oil consumption : 18.5 [kg/hr]
fuel consumption (econ. cruise speed) : 3432.4 [kg/hr] (4372.5 [litre/hr]) at 36 [%]
power
fuel burn per seat per hour (average seating) : 78.08 [litre], sfc : 90.0 [kg/KN/h]
calculation : *3* (weight) :
weight engine(s) dry : 2936.0 [kg] = 27.75 [kg/KN]
weight 78.6 litre oil tank : 6.68 [kg]
oil tank filled with 0.7 litre oil : 0.6 [kg]
oil in engine 1.3 litre oil : 1.2 [kg]
weight all fuel lines and pumps containing 54 litres fuel : 47.3 [kg]
weight engine cowling and steel fireproof bulkheads : 486.7 [kg]
weight thrust reversers : 0.0 [kg]
total weight propulsion system : 3478 [kg](9.2 [%])
***************************************************************
Accommodation cabin facilities :
typical 1-class cabin layout for 56 passengers : economy : pitch : 87.0 [cm] 34.2 [-in]
( 2+2 ) seating in 14.0 rows
weight passenger seats (width 55.5 [cm]) : 280.0 [kg]
weight cabin crew seats : 5.0 [kg]
weight flight crew seats : 63.0 [kg]
has no high density seating, only standard seating for : 56 [pax]
pax density, normal seating : 0.998 [m2/pax], high density seating : 0.998 [m2/pax]
passenger cabin luxurious spaced for good service, enough space for galleys and toilets
even at HD seating
weight 2 toilets : 61.9 [kg]
weight 1 galleys : 78.4 [kg]
weight overhead stowage for hand luggage (total : 3.0 [m3] = 63 55x35x25cm carry-on
trolleys) : 47.1 [kg]
weight 1 wardrobe closets : 13.2 [kg]
weight 30 windows (46 x 46 cm) made of acrylic glass : 127.5 [kg]
weight 2 (1.30 x 0.70 [m]) main entry doors : 54.4 [kg]
weight 1 (0.90 x 1.10 [m]) main deck freight hatch : 32.2 [kg]*
main deck space for freight/mail/luggage etc. : 14.0 [m3]
passenger compartment volume : 61 [m3]
cabin volume (usable), excluding flight deck : 85 [m3]
passenger cabin max width : 2.70 [m] cabin length : 20.70 [m] max cabin height : 1.90
[m]
floor area : 50.7 [m2], cabin width at floor : 2.45 [m]
11.3 [%] of cabin floor area is occupied by toilets & galleys, the same at high density
seating
weight cabin facilities : 762.7 [kg]
safety facilities :
evacuation time with 56 passengers : 62 [sec]
number of passengers limited by number of emergency exits
weight 2 hand fire extinguisher : 7 [kg]
central aisle : 0.48 [m] wide
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators (deploy cabin alt.>4267m): 36.4 [kg]
weight emergency flare installation : 10 [kg]
weight 2 emergency evacuation slides : 36.9 [kg]
weight safety equipment & facilities : 111 [kg]
fuselage construction :
fuselage aluminium frame : 5064 [kg]
floor loading (payload/m2): 118 [kg/m2]
weight rear pressure bulkhead : 108.3 [kg]
fuselage covering ( 194.7 [m2] duraluminium 3.18 [mm]) : 1626.0 [kg]
CSA Tu-124V at Schiphol, can be OK-TEB c/n 4 35 15 04
weight paint fuselage : 40.9 [kg]
weight aluminium floor beams : 60.6 [kg]
weight cabin furbishing : 309.6 [kg]
weight cabin floor : 707.8 [kg]
weight (sound proof) isolation : 242.9 [kg] TO-noise level : 114.0 [EPNdB]
weight 2862 [litre] main central fuel tank empty : 57.2 [kg]
weight empty 30 [litre] potable water tanks : 2.7 [kg]
weight empty waste tank : 1.4 [kg]
weight fuselage structure : 8221.2 [kg]
Avionics :
weight HF/VHF radio and Selcal : 8.0 [kg]
weight transponder : 7.0 [kg]
weight weather radar : 25.0 [kg]
Cockpit of Tu-124Sh c/n 7350610 “22” red, preserved in the Museum of Civil Aviation at Ulyanovsk , painted with fake registration CCCP-45017
weight Automatic Direction Finding (ADF) equipment : 8.0 [kg]
weight Distance Mesuring Equipment (DME) : 5.0 [kg]
weight Instrument Landing System (ILS/VOR) : 5.0 [kg]
weight SAU-1T automatic flight control System / auto-pilot : 23.0 [kg]
weight Cat I minima DH 60m RVR >=600m landing system : 15.0 [kg]
weight artificial horizons, gyro-compass, radio altimeters : 7 [kg]
weight engine monitoring gauges & control switches : 14 [kg]
weight reserve ADI, ASI, alti-meter, compass, engine temp. and rpm indicators : 15
[kg]
weight avionics : 148.0 [kg]
Systems :
Air-conditioning and pressurization system maintains sea level conditions up to 6275
[m] and gives equivalent of 2100 [m] at 11000 [m]. pressure differential : 0.57 [bar]
(kg/cm2) pressurized fuselage volume : 122 [m3] cabin air refreshment time : 2.9
[min]
weight air-conditioning and pressurization system : 71 [kg]
weight lighting : 18.5 [kg]
weight 210 [bar] hydraulic system : 10.7 [kg]
weight engine-driven 40kVA electricity generators : 14.0 [kg]
weight 22Ah battery : 28.5 [kg]
weight controls : 13.1 [kg]
weight systems : 155.4 [kg]
total weight fuselage : 9398 [kg](24.7 [%])
***************************************************************
wing construction :
total weight aluminium ribs (63 ribs) : 1416 [kg]
weight engine mounts : 53 [kg]
weight 6 wing fuel tanks empty for total 10753 [litre] fuel : 161 [kg]
weight 54 [litre] vent surge tanks : 6 [kg]
weight wing covering (painted aluminium 3.21 [mm]) : 2072 [kg]
total weight aluminium spars : 1328 [kg]
weight wings : 4817 [kg]
weight wing/square meter : 40.31 [kg]
weight bleed air thermal leading-edge anti-icing : 28.1 [kg]
Interflug Tu-124K2, referred to in East Germany as Tu-124V, DM-SDA c/n 4 35 15 08, in service from April 1965 .
weight ailerons (7.1 [m2]) : 143.4 [kg]
weight fin (8.0 [m2]) : 161.6 [kg]
weight rudder (2.9 [m2]) : 56.6 [kg]
weight tailplane (horizontal stabilizer) (21.2 [m2]): 472.3 [kg]
weight elevators (5.3 [m2]): 57.5 [kg]
weight paint wing & tail surfaces : 62.4 [kg]
weight trailing-edge double slotted flaps (17.4 [m2]) : 303.6 [kg]
weight spoilers (4.1 [m2]) : 46.6 [kg]
total weight wing construction : 6369 [kg] (28.3 [%])
*******************************************************************
landing gear :
tire pressure main wheels : 6.50 [Bar] (nitrogen), ply rating : 18 PR
tire speed limit : 364 [km/hr]
total tyre footprint : 0.14 [m2]
Runway LCN at MTOW (0.76m radius of rigidity) : 70 [ ]
Aircraft Classification Number (ACN), MTOW on rigid runway and medium subgrade strength (B) : 14 [ ]
good soft ground capabilities
wheel pressure : 4180.0 [kg]
wheel track 9.05 [m], wheelbase : 10.55 [m]
weight 8 main wheels (865 [mm] by 280 [mm]) : 641.6 [kg]
weight 2 nose wheels : 80.2 [kg]
CSA TU-124V
weight multi-disc wheel-brakes : 33.5 [kg]
weight Hydro-air flywheel detector type anti-skid units : 9.0 [kg]
weight oleo-pneumatic shock absorbers : 38.0 [kg]
weight wheel hydraulic operated retraction system : 526.3 [kg]
weight brake-chute : 25 [kg]
weight undercarriage struts (four-wheel bogies) with axle 1301.4 [kg]
total weight landing gear : 2605.1 [kg] (6.9 [%]
*******************************************************************
********************************************************************
calculated empty weight : 21851 [kg](57.5 [%])
aircraft equipment and service utensils :
weight oil for 2.9 hours flying : 68.6 [kg]
unusable fuel in engine and tanks 114.8 litre fuel : 90.1 [kg]
weight lifejackets : 25.2 [kg]
weight 1 life rafts : 35.0 [kg]
weight catering : 19.4 [kg]
weight water : 26.7 [kg]
weight crew : 324 [kg]
weight crew luggage, navigation chards, flight docs (NOTOC), manuals, miscellaneous
items : 60 [kg]
operational weight empty : 22500 [kg] (59.2 [%])
********************************************************************
useful load breakdown :
weight 56 passengers : 4312 [kg]
weight luggage : 896 [kg]
weight cargo : 792 [kg] (cargo + luggage/m3 belly : 99.2 [kg/m3])
zero fuel weight (ZFW): 28500 [kg](75.0 [%])
weight fuel for landing (1.9 hours flying) : 6500 [kg]
max. landing weight (MLW): 35000 [kg](92.1 [%])
airfields and return without need of refuelling
max. fuel weight : 33098 [kg] (87.1 [%])
payload with max fuel : 53 passengers + luggage 4902 [kg]
published maximum take-off weight : 38000 [kg] (100.0 [%])
calculation : * 4 * (engine power) :
power loading (Take-off) : 359 [kg/KN]
power loading (Take-off) 1 PUF: 718 [kg/KN]
max. total take-off power : 105.8 [KN]
calculation : *5* (loads) :
manoeuvre load : 2.1 [g] at 9000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.9 [g]
design flight time : 1.25 [hours]
design cycles : 30275 sorties, design hours : 37844 [hours]
Aeroflot Tu-124V CCCP-45070 c/n 4 35 15 09 .
average real hours flown per year unusual low : 1384 [hr], expected hours : 2000
domestic jetliner operation to remote Russian airfields were probably often not carried
out due to winter/weather/airfield conditions. Due to operation to remote airfields and
the Russian climate a higher load factor is used for strength calculations
max. wing loading (MTOW & flaps retracted) : 318 [kg/m2]
wing stress (2 g) during operation : 149 [N/kg] at 2g emergency manoeuvre
calculation : *6* (angles of attack) :
angle of attack zero lift : -1.70 ["]
max. angle of attack (stalling angle, clean) : 14.64 ["]
max. angle of attack (full flaps) : 14.23 ["]
angle of attack at economic cruise speed : 1.74 ["]
calculation : *7* (lift & drag ratios) :
lift coefficient at angle of attack 0° : 0.13 [ ]
lift coefficient at max. speed : 0.15 [ ]
lift coefficient at max. angle of attack (clean): 1.25 [ ]
max. lift coefficient ( 30 [° ] flaps) : 1.39 [ ]
CSA Tu-124V OK-UEC c/n 5 35 16 07 “ Mlada Boleslav ” taking off .
drag coefficient at max. speed : 0.0286 [ ]
drag coefficient at econ. cruise speed : 0.0313 [ ]
induced drag coefficient at econ. cruise speed : 0.0062 [ ]
drag coefficient (zero lift) : 0.0251 [ ]
lift/drag ratio at econ. speed : 5.18 [ ]
calculation : *8* (speeds) :
minimum control speed (Vmc): 274 [km/u] (147.9 [kt])
minimum unstick speed (Vmu) at TO angle 13.0 ° : 222 [km/u] (120 [kt])
take-off decision speed (V1) : 279 [km/u] (151 [kt])
take-off rotation speed (VR) : 288 [km/u] (155 [kt])
lift-off speed (VLOF) : 300 [km/u] (162 [kt]) at pitch angle : 5.7 [°]
take-off safety speed (V2) : 301 [km/u] (163 [kt])
flap retraction speed (V3) at 500m (OW loaded : 34568 [kg]): 248 [km/u] (134 [kt])
steady initial climb speed (V4) : 327 [km/u] (177 [kt])
climb speed (to FL150 with 69 [%] power) : 442 [km/hr] (239 [kt])
max. endurance speed (Vbe): 480 [km/u] min. fuel/hr : 2735 [kg/hr] at height : 7315 [m]
Interflug Tu-124V DM-SBD c/n 5 35 17 08 .
max. range speed (Vbr): 789 [km/u] (0.74 [mach]) min. fuel consumption : 4.00 [kg/km]
at cruise height : 10973 [m]
max. cruising speed : 870 [km/hr] (470 [kt]) at 10000 [m] (power:40 [%])
max. operational speed (Mmo) : 970 [km/hr] (Mach 0.87 ) at 7500 [m] (power:64 [%])
airflow at cruise speed per engine : 65.6 [kg/s]
speed of thrust jet : 2038 [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): 271 [km/u] (146 [kt])
stalling speed clean at 500 [m] height at Max.Landing Weight : 35000 [kg]): 226 [km/u]
(122 [kt])
final approach speed (landing speed) at sea-level with 30 [°] flaps VREF (max. landing
weight): 257 [km/u] (139 [kt])
ICAO Aircraft Approach Category (APC) : C
stalling speed at sea-level with 30 [°] flaps VSO (max. landing weight): 197 [km/u] (107
[kt]
stalling speed at sea-level with 30 [°] flaps VSO at 38000 [kg] AUW): 206 [km/u] (111
[kt]
Iraqi Airways Tu-124V YI-AEY. Iraq purchased two Tu-124V’s. They were destroyed during the Gulf War, early 1990 . YI-AEY was destroyed at Al Taqaddum , location : +- 500M 33°20’30”N 43°35’37”E .
rate of climb (max. continuous power) at sea-level ROC (loaded, 69 % power) : 718
[m/min]
rate of climb at sea-level ROC (loaded, 75 % power) : 851 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 80 % power on remaining
engines) : 58 [m/min]
in case of engine failure, emergency higher power rating (80.0 [%%]) can be applied on
reminding engine, but quick landing needed
rate of descent from FL240 to FL100 (7315m > 3048m): 1067 [m/min] (3501 [ft/min])
rate of descent during approach with landing gear extended, with use of spoilers: 261
[m/min] (4.4 [m/s])
calculation : *9* (regarding various performances) :
low wheel pressure, can also take off from unpaved runways
T-O run : 1306 [m]
take-off distance at sea-level gravel/packed earth field : 2031 [m]
brake-chute in tail for emergency use after engine-failure at take-off
Brake kinetic energy capacity : 613 [KW]
FAR TO runway length (TOFL) requirement at TOW 38000 [kg] standard day at SL (=
ASDA) : 2121 [m]
ICAO Aerodrome Reference. Code : 3C
Take-off flap setting : 10 [° ]
+++ FAA certification landing distance : +++
landing weight : 35000 [kg], TE flap setting : 30 [°]
runway condition : dry , landing over 50ft (15m) at threshold at sea-level
without use of thrust reversers, glideslope : 3.50 [°]
SR-422B landing field length at SL from 15 [m], dry runway, at MLW : 1628 [m] (5340
[ft])
SR-422B landing field length at SL from 15 [m], wet runway, at MLW: 1872 [m] (6141
[ft])
landing run at MLW with use of drag-chute: 943 [m] (3094 [ft])
landing field length at SL from 15 [m], dry runway, with drag-chute : 1221 [m] (4005
[ft])
Aeroflot Tu-124V with a GAZ-22 Volga station wagon in front
max. lift/drag ratio : 10.55 [ ]
climb to 5000 [m] with max payload : 6.44 [min]
climb to 10000 [m] with max payload : 19.82 [min]
descent time from 10000 [m] to 250 [m] : 24.33 [min]
max. ceiling fully loaded (mtow- 60 min.fuel): 34568 [kg] ) : 19200 [m]
ceiling limited by max. pressure differential 13825 [m]
max. theoretical ceiling (OWE + 60 min.fuel) : 20500 [m] with flying weight :25932 [kg]
calculation *10* (action radius & endurance) :
range with max. payload: 2199 [km] with 6000.0 [kg] max. useful load (89.6 [%] fuel)*
range with high density pax: 2394 [km] with 56 passengers (97.1 [%] fuel)*
range with typical two-class pax: 2394 [km] with 56 passengers (97.1 [%] fuel)*
range with max.fuel and MTOW : 2470 [km] with 4 crew and 53 passengers and 0
[kg] cargo*
ferry range (calculated): 2617 [km] with 3 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 19907 [litre] fuel : 3752 [km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 134084 [paskm]
useful load with range 1000km : 6000 [kg]
useful load with range 1000km : 56 passengers
production (theor.max load): 5220 [tonkm/hour]
production (useful load): 5220 [tonkm/hour]
production (passengers): 48720 [paskm/hour]
oil and fuel consumption per tonkm : 0.661 [kg]
calculation *11* (operating cost) :
fuel cost per hour at econ.speed (4372 [litre]):2623 [eur] (10 [pax-km/litre fuel])
fuel cost per seat 1000km flight (56 [pax] 2-class seating): 58.55 [eur/1000PK]
oil cost per hour: 77 [eur]
Aeroflot stewardess posing for a Tu-124, or Tu-104 ?? .
crew cost per hour : 450 [eur]
list price 2024 : 46 [mln USD]
average flying hours in 1 year : 1692 [hours] technical life : 22 [year]
real average service life : 22 [years]
depreciation : 22 [years] to 10% residual value
financing interest per flying hour : 613 [EUR]
write off per flying hour : 1028 [EUR]
mean time between engine failure (MTBF) : 2622 [hr]
insufficient engine reliability for ETOPS flights
can continue fly on 1 engine, low risk for emergency landing for PUF
workhours per day : 7.42 [hr]
average flight hours till crash : 0.57 [mln hr] (340 service years)
safe flight hours till fatality : 19306 [hr] (11.4 service years)
Measured tail angle from Jane’s all the world aircraft 1970-71 page 515 : 10°.
reservation pax liability/flying hour : 6.67 [SDR*] (8.34 [eur])
insurance cost per hour : 377 [eur] insurance rate : 3.7 [%]
engine maintenance cost per hour : 655.4 [eur]
wing maintenance cost per hour : 210.3 [eur]
fuselage maintenance cost per hour : 249.20 [eur]
tire life (time till worn out) : 211 [cycles]
maintenance cost per hour (excluding engines): 890 [eur]
direct operating cost per hour: 6722 [eur], DOC per km : 8.40 [eur]
DOC per seat 1000km flight (56 [pax] 2-class seating): 137.97 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 137.97 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 1.29 [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 : 4.50 [eur/pax]
airport landing fee / passenger : 4.50 [eur/pax]
retour ticket price 1000km trip : 370.43 [eur/pax]
price retour ticket Schiphol-Barcelona : 446.31 [eur/pax]
Tuesday 18 August 1970 CSA Tu-124V OK-TEB c/n 4 35 15 04
ISP Flight OK744 from Prague (PRG) to Zurich (ZRH) with 6 crew and 14 passengers.
Made an unintended wheels-up landing at Zurich-Kloten airport RW16. The aircraft touched-down on its belly and sliding for 875m down the runway. There were no casualties. The ZRH fire service used the airframe for a fire drill, set fire to it and after the drill it was cut up and disposed off. location : +- 50m 47°28’03”N 8°32’30”E .
9 fatal accidents with a total of 268 fatalities > see the accident file
Literature :
Jane s all the world aircraft 1970-71 page 514
Jane s Commercial Transport Aircraft page 233
KIJK straalverkeersvliegtuigen page 22
Wat is dat voor een vliegtuig 1963 page 232
Alles over straalverkeersvliegtuigen, Hugo Hooftman, page
Verkeersvliegtuigen nu en straks, B.vd Klaauw page
The Pushpaka’s last flight – The untold story of 4th Nov 1977 – Indian Air Force
Verkehrsflugzeuge page 109
Verkeersvliegtuigen Moussault page 67, 138
praktisch handboek vliegtuigen deel 5 page 180,181
samdimdesign.free.fr/HTML/Tu124/tu124.html
Tupolev Tu-124K of the Indian Air Force, it was used as VIP transport
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 09 February 2026 contact : info.aircraftinvestigation@gmail.com ac jetpax 2020.py python 3.7.4
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