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weight and performance calculations for the Ilyushin Il-86 CAMBER
Il-86 CCCP-86000 prototype
Ilyushin Il-86 CAMBER
role : wide-body medium-range airliner
importance : ****
first flight : 22 December 1976 CCCP-86000 prototype from Khodinka airport flown by soviet
hero A.Kuznetsov. operational : December 1980 (Aeroflot)
country : Russia
NATO reporting name : CAMBER
ICAO aircraft type designator : IL86
Design : Design bureau led by Genrik V. Nowoschilow
production : 106 aircraft, final assembly at Voronezh, USSR, WSK-Mielec in Poland built the
tail surfaces and engine pylons. Wing made in Voronezh, tail unit made in Kiev.
general information :
At the 1971 Paris Air Show the Russians revealed plans for a new wide body jetliner, indicated as Il-86, Russia’s first Airbus type wide body aircraft. Initially it was a design with 4 engines mounted at the tale, but later the engines were repositioned into four underwing pods. It was considered as replacement for the Tupolew Tu-154 jetliner. Designed for 20.000 flights and 40.000 flying hours. The Ilyushin design bureau is located at Khodinka airport, the old central Moscow airport.
The Il-86 was showed to the Western world for the first time at the 1977 Paris Air Show. Despite a busy test program the CCCP-86000 was exhibited and flown at the show.
The cabin interior was made with natural fibres materials rather than plastic for better safety in case of fire. In the West airports had been adopted to accept the high capacity widebody airliners, but the Russians choose another way by adjusting the Il-86 to the existing Russian airports. For this reason it has triple bogie main landing gear to distribute the high weight and lower the wheelpressure and secondly had entrances in the belly so passengers could embark easily without ground facilities. But this all was at the cost of a weight penalty and reduction of available cabin space, taken by integrated staircases. It was planned to have the Il-86 in service in time to carry passengers to the controversial 1980 Olympic Games in Moscow, but this deadline was not met.
On 22 September 1981 an Il-86 set a record for flying a payload of 65 ton over a 2000 km closed circuit at an average speed of 975 km/h. To achieve this ZFW needed to be around 180000 kg, MLW ca. 185000 kg and TOW 220000 kg for the occasion, or OWE was lowered by removing part of the interior, like seats etc.. Two days later the same aircraft set a record for flying 80 tons over a 1000km circuit.
The low-bypass engines were from the outset not ideal but were chosen as compromise to save time. There were plans to have it refitted with high-bypass Rolls Royce engines but this was never realized.
Only 3 aircraft were sold outside Russia, they were delivered to Chinese Xinjiang Airlines in 1990.
It was not designed for long haul flights, but it was used on long distance flights to New York or Rio de Janeiro with intermediate stops for refuelling. Later it was banned from many Western airport for its noise emission.
primary users : Aeroflot, Pulkovo, Xinjiang airlines
Accommodation:
flight crew : 4 cabin crew : 7
flight crew consist of pilot, co-pilot, navigator and flight engineer
passengers : seating for 320 in two class : 74 business class and 246 economy class seats
( 32 -in pitch) high density seating for 350 passengers
engine : 4 Kuznetsov NK-86 turbofan engines of 127.5 [KN] (28663 [lbf])
Measured chord at root : 12.17m, at tip : 3.16m fuselage length : 55.40m
dimensions :
wingspan : 48.06 [m], length overall: 59.54 [m], length of fuselage : 55.40 [m]
height : 15.81 [m] wing area : 329.8 [m^2] fuselage exterior width : 6.08 [m]
weights :
operating empty weight : 115010 [kg] max. structural payload : 41990 [kg]
Zero Fuel weight (ZFW) : 157000 [kg] max. landing weight (MLW) : 174950 [kg]
max. take-off weight : 207950 [kg] weight usable fuel : 84072 [kg] (107098 [litres])
performance :
Max. operating Mach number (Mmo) : 0.89 [Mach] (950 [km/hr]) at 10670 [m]
critical Mach speed : 0.88 [Mach]
max. cruising speed : 900 [km/hr] (Mach 0.85 ) at 10670 [m] (36 [%] power)
economic cruising speed : 871 [km/hr] (Mach 0.82 ) at 10670 [m]
service ceiling : 11500 [m]
range with max fuel and MTOW : 5000 [km] (ATA domestic fuel reserves –
820.0 [km] alternate)
description :
cantilever low-wing monoplane with retractable landing gear with nose wheel
engines attached with pylons to the wing, main landing gear attached to the wings,
fuel tanks in the wings and fuselage
Wings : three-spar structure of modified trapezoid planform, with Fowler-type double slotted
trailing edge flaps with full-span slotted LE flaps (slats) ,with spoilers airfoil : Ilyushin
average thickness/chord ratio : 10.0 [%], sweep angle 3/4 chord: 35.0 [°]
Fuselage : Pressurized conventional semi-monocoque fail safe structure of circular cross-
section built mainly of high-strength aluminium alloy
calculation : *1* (dimensions)
measured wing chord at root: 12.17 [m]
measured wing chord at tip : 3.16 [m]
taper ratio : 0.260 [ ]
mean wing chord : 6.86 [m]
wing aspect ratio : 7.00 []
Oswald factor (e): 0.674 []
seize (span*length*height) : 45240 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 15.4 [kg/hr]
fuel consumption (econ. cruise speed) : 12581.9 [kg/hr] (16027.9 [litre/hr]) at 32 [%] power
distance flown for 1 kg fuel : 0.07 [km/kg] at 10670 [m] height, sfc : 76.5 [kg/KN/h]
total fuel capacity : 107098 [litre] (84072 [kg])
calculation : *3* (weight)
weight engine(s) dry : 10160.0 [kg] = 19.92 [kg/KN]
weight 147.8 litre oil tank : 12.56 [kg]
oil tank filled with 3.2 litre oil : 2.9 [kg]
oil in engine 6.2 litre oil : 5.6 [kg]
unusable fuel in engine and tanks 160.6 litre fuel : 126.11 [kg]
weight all fuel lines and pumps containing 101 litres fuel : 330.1 [kg]
weight engine cowling : 1326.0 [kg]
weight thrust reversers : 765.0 [kg]
total weight propulsion system : 12728 [kg](6.1 [%])
***************************************************************
Accommodation cabin facilities:
typical 2-class cabin layout for 320 passengers : economy : pitch : 81.3 [cm] 32.0 [-in]
( 3+3+3 ) seating in 37.9 rows
weight passenger seats : 1742.0 [kg]
weight cabin crew seats : 35.0 [kg]
weight flight crew seats : 84.0 [kg]
weight 2 jump seats in the cockpit :14.0 [kg]
high density seating passengers : 350 [pax] at mainly 9 -abreast seating in 44.3 rows,
pitch 78.6 [cm] 30.9 [-in]
pax density, normal seating : 0.78 [m2/pax], high density seating : 0.72 [m2/pax]
passenger cabin luxurious spaced for good service, enough space for galleys and toilets even
at HD seating
weight 8 lavatories : 227.4 [kg]
weight 7 galleys : 604.8 [kg]
It was designed that passengers entered the aircraft with a stair to the lower deck. Here the passengers had to stow there luggage and winter clothing and then go up another stair to enter the upperdeck main cabin. This system became known as the “the luggage at hand system”.
weight 3 staircases from belly to maindeck : 360 [kg]
weight overhead stowage for hand luggage : 112.0 [kg]
weight 3 wardrobe closets : 32.0 [kg]
weight 3 movie screens : 68.7 [kg]
weight 78 windows (41 x 28 cm) made of acrylic glass : 212.6 [kg]
weight 11 (1.93 x 1.07 [m]) Type A main entry doors : 794.5 [kg]
weight 3 ventral stairways to belly entrance : 273.6 [kg]
weight 3 (main door size : 1.75 x 1.78 [m]) freight doors (belly) : 307.9 [kg]*
total belly baggage/cargo hold volume : 103.4 [m3]
underfloor belly hold can accommodate : 15 LD3 containers, netto volume : 66.7 [m3]
and : 21.2 [m3] bulk cargo
cabin volume (usable), excluding flight deck : 463 [m3]
passenger compartment volume : 359 [m3]
passenger cabin max width : 5.70 [m] cabin length : 44.67 [m] max cabin height : 2.61 [m]
floor area : 250.8 [m2]
weight cabin facilities : 4594.9 [kg]
safety facilities:
evacuation time with 350 passengers : 31 [sec]
weight 15 hand fire extinguisher : 45 [kg]
weight cockpit voice recorder (CVR) and flight data recorder (FDR): 20.0 [kg]
weight oxygen masks & oxygen generators (deploy cabin alt.>4267m): 208.0 [kg]
weight emergency flare installation : 10 [kg]
weight 8 emergency evacuation slides : 321.6 [kg]
weight safety equipment & facilities : 878 [kg]
fuselage construction:
fuselage aluminium frame : 26656 [kg]
floor loading (payload/m2): 167 [kg/m2]
weight rear pressure bulkhead : 516.8 [kg]
fuselage covering ( 876.4 [m2] duraluminium 3.41 [mm]) : 7976.5 [kg]
weight floor beams : 4252.0 [kg]
weight cabin furbishing : 4030.5 [kg]
weight cabin floor : 3897.5 [kg]
weight (sound proof) isolation : 887.2 [kg] TO-noise level : 105.7 [EPNdB]
weight 19999 [litre] main central fuel tanks empty : 400.0 [kg]
weight empty 506 [litre] potable water tanks : 44.8 [kg]
weight empty waste tank : 19.4 [kg]
weight fuselage structure : 48680.3 [kg]
Avionics:
weight VHF radio and Selcal : 9.0 [kg]
weight flight and service attendants intercom : 5.0 [kg]
weight monochromatic weather X-band (3.2cm wavelength) radar system : 25.0 [kg]
Cockpit of Il-86 RA-86103
weight VOR/ILS,RMI,DME,radio altimeter, ASI, time clock : 20.0 [kg]
weight SAU-1T-2 automatic flight control System / auto-pilot : 23.0 [kg]
weight Pizhma-1 navigational system with OMEGA inputs : 15.0 [kg]
weigh ILS-couple airfield approach aids for ICAO Cat.II landing : 10 [kg]
weight artificial horizons, compass, alti-meters : 7 [kg]
weight engine monitoring gauges & control switches : 28 [kg]
weight Performance Management System (PMS) : 12 [kg]
weight reserve ADI, ASI, alti-meter, compass, engine temp. and rpm indicators : 15 [kg]
weight avionics : 175.0 [kg]
Systems:
Air-conditioning and pressurization system maintains sea level conditions up to 7350 [m]
and gives equivalent of 2100 [m] at 13000 [m]. pressure differential : 0.63 [bar] (kg/cm2)
pressurized fuselage volume : 1002 [m3] cabin air refreshment time : 3.3 [min]
weight air-conditioning and pressurization system : 510 [kg]
weight APU / engine starter: 63.8 [kg]
weight lighting : 105.6 [kg]
weight triple redundant 207 bar hydraulic system : 153.0 [kg]
weight three engine-driven 90kVA 400 Hertz electricity generators : 80.0 [kg]
weight integrated drive generator (IDG) : 25 [kg]
weight three 24V 25Ah nickel-cadmium batteries : 37.0 [kg]
weight controls : 22.9 [kg]
weight systems : 997.0 [kg]
total weight fuselage : 55325 [kg](26.6 [%])
***************************************************************
total weight aluminium ribs (1548 ribs) : 7416 [kg]
weight engine mounts : 255 [kg]
weight 6 wing fuel tanks empty for total 87099 [litre] fuel : 1306 [kg]
weight 428 [litre] vent surge tanks : 51 [kg]
weight wing covering (painted aluminium 4.61 [mm]) : 8218 [kg]
total weight aluminium spars (multi-cellular wing structure) : 8473 [kg]
weight wings : 24107 [kg]
weight wing/square meter : 73.09 [kg]
weight thermal leading-edge anti-icing : 52.9 [kg]
weight high & low speed ailerons (19.16 [m2]) : 701.7 [kg]
Entering Atlant-Soyuz Airlines Il-86 RA-86109 via the tail-entrance at Vnukovo aiport(VKO), August 2009 for a flight to Sochi Adler.
weight fin (39.18 [m2]) : 1435.0 [kg]
weight rudder (20.62 [m2]) : 725.1 [kg]
weight tailplane (stabilizer) (36.02 [m2]): 1451.1 [kg]
weight elevators (8.65 [m2]): 170.97 [kg]
weight flight control hydraulic servo actuators: 75.4 [kg]
weight trailing-edge double slotted flaps (79.15 [m2]) : 2464.0 [kg]
weight leading edge slats (30.38 [m2]) : 613.9 [kg]
weight spoilers (11.2 [m2]) : 204.3 [kg]
total weight wing construction : 33614 [kg] (29.2 [%])
*******************************************************************
tire pressure main wheels : 11.50 [Bar] (nitrogen), ply rating : 26 PR
tire speed limit : 364 [km/hr]
total tyre footprint : 1.07 [m2]
Runway LCN at MTOW (0.76m radius of rigidity) : 50 [ ]
Aircraft Classification Number (ACN), MTOW on rigid runway and medium
subgrade strength (B) : 24 [ ] good soft ground capabilities
wheel pressure : 15249.7 [kg]
weight 12 main wheels (1300 [mm] by 477 [mm]) : 1582.4 [kg]
Passengers boarding Pulkovo IL-86 RA-86092
weight 2 nose wheels : 131.9 [kg]
weight hydraulic disc wheel-brakes : 157.0 [kg]
weight Duplex anti-skid units : 12.6 [kg]
weight oleo-pneumatic shock absorbers : 209.3 [kg]
weight wheel hydraulic operated retraction system : 2190.0 [kg]
weight undercarriage struts (six-wheel bogies) with axle 6557.3 [kg]
total weight landing gear : 10840.4 [kg] (5.2 [%]
*******************************************************************
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calculated empty weight : 112508 [kg](54.1 [%])
weight oil for 6.7 hours flying : 123.1 [kg]
weight lifejackets : 144.0 [kg]
weight 6 life rafts : 200.0 [kg]
weight catering : 560.0 [kg]
weight water : 448.0 [kg]
weight crew : 891 [kg]
weight crew luggage, nav. chards, flight doc., miscell. items : 136 [kg]
operational weight empty : 115010 [kg] (55.3 [%])
********************************************************************
weight 320 passengers : 24640 [kg]
weight luggage : 5120 [kg]
weight cargo : 12230 [kg] (cargo + luggage/m3 belly : 155 [kg/m3])
zero fuel weight (ZFW): 157000 [kg](75.5 [%])
weight fuel for landing (1.4 hours flying) : 17950 [kg]
max. landing weight (MLW): 174950 [kg](84.1 [%])
max. fuel weight : 199082 [kg] (95.7 [%])
payload with max fuel : 95 passengers + luggage 8868 [kg]
published maximum take-off weight : 207950 [kg] (100.0 [%])
Aeroflot IL-86 CCCP-86003 at the 1981 Paris air Show at le Bourget airport.
calculation : * 4 * (engine power)
power loading (Take-off) : 408 [kg/KN]
power loading (Take-off) 1 PUF: 544 [kg/KN]
max. total take-off power : 510.0 [KN]
calculation : *5* (loads)
manoeuvre load : 1.1 [g] at 9000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.4 [g]
design flight time : 3.50 [hours]
design cycles : 16720 sorties, design hours : 58520 [hours]
max. wing loading (MTOW & flaps retracted) : 631 [kg/m2]
wing stress (2 g) during operation : 156 [N/kg] at 2g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.81 ["]
max. angle of attack (stalling angle, clean) : 13.72 ["]
max. angle of attack (full flaps) : 17.67 ["]
angle of attack at max. speed : 3.39 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.15 [ ]
lift coefficient at max. speed : 0.43 [ ]
lift coefficient at max. angle of attack (clean): 1.29 [ ]
max. lift coefficient full flaps : 1.90 [ ]
drag coefficient at max. speed : 0.0463 [ ]
drag coefficient at econ. cruise speed : 0.0449 [ ]
induced drag coefficient at econ. cruise speed : 0.0133 [ ]
drag coefficient (zero lift) : 0.0316 [ ]
lift/drag ratio at econ. speed : 9.31 [ ]
calculation : *8* (speeds
take-off decision speed (V1) : 269 [km/u] (145 [kt])
take-off rotation speed (VR) : 294 [km/u] (159 [kt])
minimum unstick speed (Vmu) at TO angle 10.0 ° : 298 [km/u] (161 [kt])
Aeroflot Il-86 RA-86095 taking of from Moscow Sheremetyevo airport. The Il-86 was designed to operate from airfields only 2600m long. But with 208.000 kg TOW calculated runway length is 3285m. To operate from 2600m runways is only possible with reduced TOW.
lift-off speed (VLOF) : 327 [km/u] (177 [kt]) at pitch angle : 7.7 [°]
take-off safety speed (V2) : 330 [km/u] (178 [kt])
flap retraction speed (V3) at 500m (OW loaded : 195368 [kg]): 337 [km/u] (182 [kt])
steady initial climb speed (V4) : 356 [km/u] (192 [kt])
climb speed (to FL150 with 78 [%] power) : 550 [km/hr] (297 [kt])
max. endurance speed (Vbe): 553 [km/u] min. fuel/hr : 11488 [kg/hr] at height : 6706 [m]
max. range speed (Vbr): 888 [km/u] (0.83 [mach]) min. fuel consumption : 14.93 [kg/km] at cruise height : 10058 [m]
max. cruising speed : 900 [km/hr] (486 [kt]) at 10670 [m] (power:33 [%])
max. operational speed (Mmo) : 950 [km/hr] (Mach 0.89 ) at 10670 [m] (power:37 [%])
airflow at cruise speed per engine : 155.6 [kg/s]
speed of thrust jet : 1879 [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): 330 [km/u] (178 [kt])
stalling speed clean at 500 [m] height at Max.Landing Weight : 174950 [kg]): 300 [km/u]
(162 [kt])
final approach speed (landing speed) at sea-level with full flaps VREF (max. landing weight):
278 [km/u] (150 [kt])
ICAO Aircraft Approach Category (APC) : D
stalling speed at sea-level with full flaps VSO (max. landing weight): 214 [km/u] (116 [kt]
rate of climb at sea-level ROC (loaded, 78 % power) : 963 [m/min]
rate of climb at sea-level ROC (loaded, 75 % power) : 894 [m/min]
rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 100 % power on remaining
engines) : 773 [m/min]
can not stay on height 1000 [m] with 2 engines out, immediate emergency landing needed
rate of descent from FL240 to FL100 (7315m > 3048m): 914 [m/min] (2999 [ft/min])
rate of descent during approach with landing gear extended, with use of spoilers: 457
[m/min] (8 [m/s])
calculation : *9* (regarding various performances)
low wheel pressure, can also take off from unpaved runways
take-off distance at sea-level gravel/packed earth field : 3430 [m]
ICAO Aerodrome Reference Code : 4D
Brake kinetic energy capacity : 2296 [KW]
Siberian Airlines IL-86 takes off from Tivat Airport , Montenegro, 2007. The Il-86 needs high flap setting for short take-offs
FAR TO balanced runway length (TOFL) requirement at TOW 207950 [kg] standard day at
SL (distance to 10.7m height x 1.15): 3287 [m]
+++ FAA certification landing distance : +++
landing weight : 174950 [kg], TE flap setting : 40 [°]
runway condition : dry , landing over 50ft (15m) at threshold at sea-level
without use of thrust reversers
FAA approved landing field length : 1917 [m] (6289 [ft])
landing distance (C.A.R.) from 15 [m] at SL, wet runway: 2196 [m] (7204 [ft])
max. lift/drag ratio : 10.83 [ ]
climb to 5000 [m] with max payload : 4.80 [min]
climb to 10000 [m] with max payload : 14.78 [min]
descent time from 10000 [m] to 250 [m] : 24.33 [min]
ceiling limited by max. pressure differential 17025 [m]
theoretical ceiling fully loaded (mtow- 60 min.fuel: 195368 [kg] ) : 15900 [m]
Ural Airlines IL-86 RA-86093 c/n 51483207064
calculation *10* (action radius & endurance)
range with max. payload: 3321 [km] with 41990.0 [kg] max. useful load (60.6 [%] fuel)*
range with high density pax: 4005 [km] with 350 passengers (71.8 [%] fuel)*
range with typical two-class pax: 4212 [km] with 320 passengers (75.1 [%] fuel)*
range with max.fuel : 5820 [km] with 11 crew and 95 passengers and 100.0 [%] fuel*
ferry range (calculated): 6038 [km] with 4 crew and zero payload (100.0 [%] fuel)*
max range theoretically with additional fuel tanks total 120401 [litre] fuel : 6665 [km]*
* calculated ranges without fuel reserves
Available Seat Kilometres (ASK) : 1406019 [paskm]
useful load with range 1000km : 41990 [kg]
useful load with range 1000km : 350 passengers
production (theor.max load): 37791 [tonkm/hour]
production (useful load): 37791 [tonkm/hour]
production (passengers): 313553 [paskm/hour]
oil and fuel consumption per tonkm : 0.333 [kg]
calculation *11* (operating cost)
fuel cost per hour (16028 [litre]):9616 [eur] (20 [pax-km/litre fuel])
fuel cost per seat 1000km flight (348 [pax] 2-class seating): 30.67 [eur/1000PK]
oil cost per hour: 64 [eur]
crew cost per hour : 1500 [eur]
list price 2024 : 172 [mln USD]
China Xinjiang airlines Il-86 B-2018
average flying hours in 1 year : 1500 [hours] technical life : 39 [year]
real average service life : 20 [years]
depreciation - 20 [years] to 10% residual value
economic hours (expected total flying hours): 30000 [hours] is 0 [%] less
then cor. design hours 30000 [hours]
financing interest per flying hour : 2582 [EUR]
write off per flying hour : 4766 [EUR]
time between engine failure : 10513 [hr]
can continue fly on 3 engines, low risk for emergency landing for PUF
workhours per day : 4.99 [hr]
average flight hours till crash : 1.59 [mln hr] (1060 service years)
safe flight hours till fatality : 198750 [hr] (132.5 service years)
reservation pax liability/flying hour : 0.65 [SDR*] (0.81 [eur])
insurance cost per hour : 498 [eur] insurance rate : 1.2 [%]
engine maintenance cost per hour : 281.6 [eur]
wing maintenance cost per hour : 207.3 [eur]
fuselage maintenance cost per hour : 143.09 [eur]
tire life (time till worn out) : 90 [cycles]
maintenance cost per hour (excluding engines): 2133 [eur]
direct operating cost per hour: 21442 [eur], DOC per km : 24.62 [eur]
DOC per seat 1000km flight (348 [pax] 2-class seating): 68.38 [eur/1000PK]
DOC per seat 1000km flight (high density seating): 68.07 [eur/1000PK]
DOC per kg cargo for a 1000km flight : 0.57 [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 : 3.67 [eur/pax]
airport landing fee / passenger : 3.67 [eur/pax]
retour ticket price 1000km trip : 213.70 [eur/pax]
price retour ticket Schiphol-Barcelona : 251.31 [eur/pax]
Il-86 RA-86074 pictured at Palma de Mallorca, July 1995. The aircraft was written of in a not intended wheels-up landing at Dubai airport, RW30R, with no fatalities, September 2001.
accidents with fatalities > see the accident file
Literature :
Observers Airliners page121,122
Flugzeuge der Welt page 132,133
Advanced jetliners page 46 - 52
https://contentzone.eurocontrol.int/aircraftperformance/default.aspx?
Jane’s all the world aircraft 1979-80 page 188
Air international apr’94
Verkeersvliegtuigen blz. 57
IL-86: the first Soviet "Airbus" (topwar.ru)
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 13 May 2024 contact : info.aircraftinvestigation@gmail.com ac jetpax 2020.py python 3.7.4
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