Aircraft investigation >>>>>>> HOME PAGE

weight and performance calculations for the Boeing 720B

Alia – Royal Jordanian Airlines Boeing 720-030B at Schiphol, could be JY-ADS..

Boeing 720B

role : jet airliner

importance : ****

first flight : 6 October 1960 operational : April 1961 (American Airlines)

country : United States of America

ICAO aircraft type designator : B720

design :

production : 89 720B aircraft

general information :

This version is equipped with the more efficient and quieter turbofan engines instead of the turbojets in the 720. The turbofans are 15% more economical. The 720B was the most versatile of the 707 family, it was economical, had high performance with sufficient range.

primary users : American Airlines (8), Lufthansa (8), Northwest Orient Airlines (6), Ethiopian

Airlines, Pakistan Int’l, El Al (2), Saudi Arabian Airlines, Panam (3) Continental (6),

Western Airlines (17)

Accommodation:

flight crew : 3 cabin crew : 6

flight crew consist of , co-pilot and flight engineer

passengers : seating for 137 in two class : 18 first class and 119 coach class seats ( 34 -in pitch)

maximum seating capacity : 156 passengers

engine : 4 Pratt & Whitney JT3D-1 turbofan engines of 75.71 [KN] (17020 [lbf])

Measured chord at wing root : 10.01 [m]

.

dimensions :

wingspan : 39.87 [m], length overall: 41.72 [m], length of fuselage : 40.79 [m] height : 12.47 [m]

wing area gross : 226.04 [m^2] fuselage exterior width : 3.76 [m]

weights :

empty weight : 49705 [kg]

operating empty weight : 52390 [kg] max. structural payload : 18370 [kg]

Zero Fuel weight (ZFW) : 70760 [kg] max. landing weight (MLW) : 79380 [kg]

max. take-off weight : 106140 [kg] weight usable fuel : 48120 [kg] (61300 [litres])

performance :

Max. operating Mach number (Mmo) : 0.908 [Mach] (1010 [km/hr]) at 7620 [m]

critical Mach speed : 0.87 [Mach]

max. cruising speed : 940 [km/hr] (Mach 0.90 ) at 12150 [m] (36 [%] power)

economic cruising speed : 897 [km/hr] (Mach 0.86 ) at 12150 [m]

service ceiling : 12350 [m]

range with max fuel and MTOW : 7686 [km] (ATA domestic fuel reserves - 370.0 [km]

alternate)

Northwest N721US B720-051B c/n 18351

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 : all-metal two spar fail-safe wing structure

with trailing edge Fowler flaps with leading edge Kruger flaps outboard of the inboard engines ,with spoilers airfoil : NACA

average thickness/chord ratio : 12.0 [%], sweep angle 3/4 chord: 34.0 [°]

incidence at root : 2.00 [°], dihedral : 7.0 [°]

calculation : *1* (dimensions)

measured wing chord at root: 10.01 [m]

measured wing chord at tip : 3.61 [m]

taper ratio : 0.361 [ ]

mean wing chord : 5.67 [m]

wing aspect ratio : 7.03 []

Oswald factor (e): 0.666 []

seize (span*length*height) : 20742 [m^3]

calculation : *2* (fuel consumption)

oil consumption : 4.2 [kg/hr]

fuel consumption (econ. cruise speed) : 5358.0 [kg/hr] (6825.5 [litre/hr]) at 22 [%] power

distance flown for 1 kg fuel : 0.17 [km/kg] at 12150 [m] height, sfc : 79.2 [kg/KN/h]

total fuel capacity : 61300 [litre] (48120 [kg])

calculation : *3* (weight)

weight engine(s) dry : 7556.0 [kg] = 24.95 [kg/KN]

weight 3210 litre de-mineralized water tank for engine injection : 272.86 [kg]

weight 57.3 litre oil tank : 4.87 [kg]

oil tank filled with 1.9 litre oil : 1.7 [kg]

oil in engine 3.7 litre oil : 3.3 [kg]

weight all fuel lines and pumps containing 84 litres fuel : 110.4 [kg]

weight engine cowling : 787.4 [kg]

weight ejector rings : 151.4 [kg]

total weight propulsion system : 8888 [kg](8.4 [%])

***************************************************************

Accommodation cabin facilities:

High density seating is limited to 149 passengers with 2 overwing exits, for the 720 number of pax is limited by max. payload at 152 passengers. With 4 overwing exits max. allowed pax is 156 but this could be only of use for the 720B with higher payload.

typical 2-class cabin layout for 137 passengers : economy : pitch : 86.4 [cm] 34.0 [-in] ( 3+3 )

seating in 24.3 rows

first class pitch : 101.6 [cm] 40.0 [-in] at 4 -abreast

weight passenger seats (width 51.2 [cm]) : 767.6 [kg]

weight cabin crew seats : 30.0 [kg]

weight flight crew seats : 63.0 [kg]

high density seating passengers : 156 [pax] at mainly 6 -abreast seating in 26.9 rows, pitch

83.8 [cm] 33.0 [-in]

pax density, normal seating : 0.762 [m2/pax], high density seating : 0.669 [m2/pax]

weight 4 lavatories : 114.0 [kg]

weight 3 galleys : 131.8 [kg]

Northwest airlines interior

weight overhead stowage for hand luggage (total : 8.3 [m3] = 172 55x35x25cm carry-on

trolleys) : 129.2 [kg]

weight 2 wardrobe closets : 37.1 [kg]

weight 10 movie screens : 78.3 [kg]

weight 51 windows (47x38cm) made of acrylic glass: 215.4 [kg]

weight 2 (1.83 x 0.88 [m]) main entry doors : 96.7 [kg]

weight 2 (1.22 x 0.61 [m]) galley service doors : 44.9 [kg]

weight 2 (main door size : 1.30 x 1.22 [m]) freight doors (belly) : 104.0 [kg]*

total usable belly baggage/cargo hold volume : 39.1 [m3]

cabin volume (usable), excluding flight deck : 199 [m3]

passenger compartment volume : 129 [m3]

passenger cabin max width : 3.55 [m] cabin length : 29.41 [m] max cabin height : 2.19 [m]

floor area : 93.2 [m2]

weight cabin facilities : 1812.0 [kg]

safety facilities:

weight 4 type III over wing emergency exits (51x91 cm): 59.2 [kg]

evacuation time with 156 passengers : 47 [sec]

weight 4 hand fire extinguisher : 11 [kg]

weight oxygen masks & oxygen generators (deploy cabin alt.>4267m): 89.0 [kg]

weight emergency flare installation : 10 [kg]

weight 4 emergency evacuation slides : 117.1 [kg]

weight safety equipment & facilities : 287 [kg]

fuselage construction:

fuselage aluminium frame : 9263 [kg]

floor loading (payload/m2): 197 [kg/m2]

weight rear pressure bulkhead : 164.7 [kg]

fuselage covering ( 353.1 [m2] duraluminium 2.80 [mm]) : 2598.9 [kg]

weight paint fuselage : 74.1 [kg]

weight aluminium floor beams : 445.9 [kg]

weight cabin furbishing : 820.6 [kg]

weight cabin floor : 1372.4 [kg]

weight (sound proof) isolation : 431.7 [kg] TO-noise level : 113.2 [EPNdB]

weight 23313 [litre] main central fuel tank empty : 466.3 [kg]

weight empty 206 [litre] potable water tanks : 18.2 [kg]

weight empty waste tank : 11.5 [kg]

weight fuselage structure : 15667.4 [kg]

Avionics:

weight radio transceiver equipment : 7.0 [kg]

weight weather radar : 25.0 [kg]

weight Doppler & radio direction finding (RDF) equipment : 5.0 [kg]

weight Sperry automatic flight control system, with SP-30 auto-pilot : 25.0 [kg]

Northwest Airlines 720B N721US cockpit

weight Cat III auto-landing system : 15.0 [kg]

weight artificial horizons, compass, alti-meters : 7 [kg]

weight engine monitoring gauges & control switches : 28 [kg]

weight reserve ADI, ASI, alti-meter, compass, engine temp. and rpm indicators : 15 [kg]

weight avionics : 133.0 [kg]

Systems:

Air-conditioning and pressurization system maintains sea level conditions up to 6775 [m]

and gives equivalent of 2000 [m] at 11600 [m]. pressure differential : 0.60 [bar] (kg/cm2)

pressurized fuselage volume : 343 [m3] cabin air refreshment time : 3.1 [min]

weight air-conditioning and pressurization system : 189 [kg]

weight lighting : 45.2 [kg]

weight 210 bar hydraulic system : 105.2 [kg]

Boeing 720-051B SX-DBN “Nestos” c/n 18688/361

weight engine-driven 40kVA electricity generators : 34.2 [kg]

weight 22Ah battery : 28.5 [kg]

weight controls : 18.0 [kg]

weight systems : 419.8 [kg]

total weight fuselage : 18319 [kg](17.3 [%])

***************************************************************

total weight aluminium ribs (34 ribs) : 3426 [kg]

weight engine mounts : 151 [kg]

weight 6 wing fuel tanks empty for total 38232 [litre] fuel : 573 [kg]

weight 245 [litre] vent surge tanks : 29 [kg]

weight wing covering (painted aluminium 3.19 [mm]) : 3896 [kg]

total weight aluminium spars (multi-cellular wing structure) : 3444 [kg]

weight wings : 10767 [kg]

weight wing/square meter : 47.63 [kg]

weight bleed air thermal leading-edge anti-icing : 43.9 [kg]

weight ailerons (11.2 [m2]) : 266.7 [kg]

weight fin (30.5 [m2]) : 727.7 [kg]

weight rudder (9.5 [m2]) : 217.4 [kg]

weight tailplane (horizontal stabilizer) (44.0 [m2]): 1156.7 [kg]

weight elevators (10.4 [m2]): 134.0 [kg]

weight paint wing & tail surfaces : 126.2 [kg]

weight flight control hydraulic servo actuators: 34.6 [kg]

American Airlines Boeing 720B, can be N7527A ?

weight trailing-edge single slotted Fowler flaps (33.6 [m2]) : 524.4 [kg]

weight leading edge Kruger flaps (2.5 [m2]) : 31.8 [kg]

weight spoilers (10.5 [m2]) : 126.8 [kg]

total weight wing construction : 14911 [kg] (28.5 [%])

*******************************************************************

tire pressure main wheels : 10.20 [Bar] (nitrogen), ply rating : 22 PR

tire speed limit : 364 [km/hr]

total tyre footprint : 0.37 [m2]

Runway LCN at MTOW (0.76m radius of rigidity) : 74 [ ]

Aircraft Classification Number (ACN), MTOW on rigid runway and medium subgrade

strength (B) : 36 [ ]

Can also operate from unpaved runways subgrade B

wheel pressure : 11675.4 [kg]

wheel track : 6.68 [m] wheelbase : 15.44 [m]

weight 8 Dunlop 40.0 x 14.0 main wheels (1016 [mm] by 356 [mm]) : 704.9 [kg]

weight 2 nose wheels : 88.1 [kg]

weight multi-disc wheel-brakes : 83.2 [kg]

weight Hydro-air flywheel detector type anti-skid units : 9.0 [kg]

weight oleo-pneumatic shock absorbers : 94.3 [kg]

weight wheel hydraulic operated retraction system : 1116.3 [kg]

weight undercarriage struts (four-wheel bogies) with axle 3430.0 [kg]

total weight landing gear : 5525.9 [kg] (5.2 [%]

*******************************************************************

El Al Boeing 720-058B 4X-ABB c/n 18425/290, it was hijacked 18 February 1969.

El Al Flight LY432, was a scheduled service from Amsterdam (AMS), the Netherlands to Tel Aviv (TLV), Israel, with an intermediate stop at Zürich (ZRH), Switzerland.
The airplane, a Boeing 720, was taxiing for takeoff at Zürich when it was attacked by a squad of four armed Palestinian militants, members of the Lebanese-based militant organization Popular Front for the Liberation of Palestine. Several of the crew members were injured during the attack and the plane was severely damaged. The co-pilot, Yoram Peres, died of his wounds a month later.
An undercover Israeli security guard who stationed on the plane, Mordechai Rahamim, opened fire at the attackers, killing one. (source : aviation safety network)

El Al Flight 432 attack - Wikipedia

********************************************************************

calculated empty weight : 47644 [kg](44.9 [%])

weight oil for 9.8 hours flying : 45.7 [kg]

weight engine injection water : 3210.1 [kg]

unusable fuel in engine and tanks 245.2 litre fuel : 192.5 [kg]

weight lifejackets : 61.6 [kg]

weight 2 life rafts : 85.6 [kg]

weight catering : 132.0 [kg]

weight water : 182.2 [kg]

weight crew : 729 [kg]

weight crew luggage, navigation chards, flight docs (NOTOC), manuals, miscellaneous items : 108 [kg]

operational weight empty : 52390 [kg] (49.4 [%])

********************************************************************

weight 137 passengers : 10549 [kg]

weight luggage : 2192 [kg]

weight cargo : 5629 [kg] (cargo + luggage/m3 belly : 165 [kg/m3])

zero fuel weight (ZFW): 70760 [kg](66.7 [%])

weight fuel for landing (1.6 hours flying) : 8620 [kg]

max. landing weight (MLW): 79380 [kg](74.8 [%])

max. fuel weight : 100510 [kg] (94.7 [%])

payload with max fuel : 61 passengers + luggage 5630 [kg]

published maximum take-off weight : 106140 [kg] (100.0 [%])

Pakistan International Airlines Boeing 720-040B, probably AP-AMG, newly delivered from Boeing. Later it flew for Air Malta.

calculation : * 4 * (engine power)

power loading (Take-off) : 350 [kg/KN]

power loading (Take-off) 1 PUF: 467 [kg/KN]

max. total take-off power : 302.8 [KN]

calculation : *5* (loads)

manoeuvre load : 1.7 [g] at 9000 [m]

limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.2 [g]

design flight time : 1.85 [hours]

design cycles : 25600 sorties, design hours : 47360 [hours]

max. wing loading (MTOW & flaps retracted) : 470 [kg/m2]

wing stress (2 g) during operation : 169 [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) : 13.66 ["]

max. angle of attack (full flaps) : 16.90 ["]

angle of attack at economic cruise speed : 2.61 ["]

calculation : *7* (lift & drag ratios

lift coefficient at angle of attack 0° : 0.15 [ ]

lift coefficient at max. speed : 0.19 [ ]

lift coefficient at max. angle of attack (clean): 1.28 [ ]

max. lift coefficient 30 [° ] flap setting : 1.84 [ ]

Boeing 720-023(B) G-BCBA c/n 18014 of Monarch Airlines. This aircraft was delivered to American Airlines in July 1960 as a 720 and was later converted to 720B

drag coefficient at max. speed : 0.0281 [ ]

drag coefficient at econ. cruise speed : 0.0308 [ ]

induced drag coefficient at econ. cruise speed : 0.0091 [ ]

drag coefficient (zero lift) : 0.0217 [ ]

lift/drag ratio at econ. speed : 6.64 [ ]

calculation : *8* (speeds

minimum unstick speed (Vmu) at TO angle 12.5 ° : 261 [km/u] (141 [kt])

take-off decision speed (V1) : 257 [km/u] (139 [kt])

take-off rotation speed (VR) : 270 [km/u] (146 [kt])

lift-off speed (VLOF) : 293 [km/u] (158 [kt]) at pitch angle : 9.5 [°]

take-off safety speed (V2) : 296 [km/u] (160 [kt])

flap retraction speed (V3) at 500m (OW loaded : 100782 [kg]): 294 [km/u] (159 [kt])

steady initial climb speed (V4) : 322 [km/u] (174 [kt])

climb speed (to FL150 with 66 [%] power) : 558 [km/hr] (301 [kt])

max. endurance speed (Vbe): 669 [km/u] min. fuel/hr : 4892 [kg/hr] at height : 10973 [m]

Color postcard depicting photographic image of Ecuatoriana de Aviacion Boeing 720B in flight; three-quarter rear view; “Isla de Galapagos” livery by Bolivar Mena Franco .

Boeing 720-023B HC-AZP c/n 18036/215

max. range speed (Vbr): 882 [km/u] (0.84 [mach]) min. fuel consumption : 6.18 [kg/km] at

cruise height : 11582 [m]

max. cruising speed : 940 [km/hr] (508 [kt]) at 12150 [m] (power:27 [%])

max. operational speed (Mmo) : 1010 [km/hr] (Mach 0.91 ) at 7620 [m] (power:44 [%])

airflow at cruise speed per engine : 117.1 [kg/s]

speed of thrust jet : 1566 [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): 269 [km/u] (145 [kt])

stalling speed clean at 500 [m] height at Max.Landing Weight : 79380 [kg]): 244 [km/u] (132

[kt])

Cypres Airways Boeing 720-23(B) G-BCBB c/n 18013 approaching. It flew also with Air Ceylon under registration 4X-JYG

final approach speed (landing speed) at sea-level with full flaps VREF (max. landing weight):

243 [km/u] (131 [kt])

ICAO Aircraft Approach Category (APC) : C

stalling speed at sea-level with full flaps VSO (max. landing weight): 187 [km/u] (101 [kt]

rate of climb (max. continous power) at sea-level ROC (loaded, 66 % power) : 1125 [m/min]

rate of climb at sea-level ROC (loaded, 75 % power) : 1421 [m/min]

rate of climb at 1000 [m] with 1 engine out (PUF/MTOW, 66 % power on remaining

engines) : 501 [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)

Brake kinetic energy capacity : 1591 [KW]

CAR takeoff runway length at MTOW 106140 kg, at sea level, standard day : 7550 ft > 2300m, according to Jane’s it is 1885m, calculated 1895m. Boeing 707-120B : 2270m, calculated 2352m..checking for the 707-120B difference between Jane’s and Boeing it is about 200m , making TO distance around 2100m..

FAR TO runway length (TOFL) requirement at TOW 106140 [kg] standard day at SL

(= ASDA) : 1895 [m]

Take-off flap setting : 10 [° ]

+++ FAA certification landing distance : +++

landing weight : 79380 [kg], TE flap setting : 30 [°]

runway condition : dry , landing over 50ft (15m) at threshold at sea-level

without use of thrust reversers

Approach speed at max. landing weight 132 knots > 244 km/h, CAR landing runway length from 15m :

6350 ft = 1935 [m], Jane’s 1964-65 : landing run 825m (2710ft), calculated 1152m..but this is actual distance/ 0.6

CAR landing runway length at SL from 15 [m], dry runway : 1933 [m] (6344 [ft])

CAR landing runway length at SL from 15 [m], wet runway: 2179 [m] (7147 [ft])

max. lift/drag ratio : 13.03 [ ]

climb to 5000 [m] with max payload : 4.11 [min]

climb to 10000 [m] with max payload : 12.66 [min]

descent time from 10000 [m] to 250 [m] : 24.33 [min]

max. ceiling fully loaded (mtow- 60 min.fuel): 100782 [kg] ) : 17600 [m]

ceiling limited by max. pressure differential 15200 [m]

max. theoretical ceiling (OWE + 60 min.fuel) : 20300 [m] with flying weight :57748 [kg]

calculation *10* (action radius & endurance)

range with max. payload: 5378 [km] with 18370.0 [kg] max. useful load (73.5 [%] fuel)*

range with high density pax: 6050 [km] with 156 passengers (81.5 [%] fuel)*

range with typical two-class pax: 6364 [km] with 137 passengers (85.2 [%] fuel)*

Range with max fuel : 4350 [nm] = 8056 [km] , - 200 [nm] (370 km) reserve = 7686 [km] T-O wgt 234340 lb = 106.296 [kg]

range with max.fuel and MTOW : 7663 [km] with 9 crew and 61 passengers and 0 [kg] cargo*

ferry range (calculated): 8021 [km] with 3 crew and zero payload (100.0 [%] fuel)*

max range theoretically with additional fuel tanks total 69491 [litre] fuel : 8889 [km]*

* calculated ranges without fuel reserves

Available Seat Kilometres (ASK) : 935123 [paskm]

useful load with range 1000km : 18370 [kg]

useful load with range 1000km : 156 passengers

production (theor.max load): 17268 [tonkm/hour]

production (useful load): 17268 [tonkm/hour]

production (passengers): 144317 [paskm/hour]

oil and fuel consumption per tonkm : 0.311 [kg]

calculation *11* (operating cost)

fuel cost per hour (6825 [litre]):4095 [eur] (21 [pax-km/litre fuel])

fuel cost per seat 1000km flight (154 [pax] 2-class seating): 28.37 [eur/1000PK]

oil cost per hour: 18 [eur]

crew cost per hour : 1200 [eur]

list price 2024 : 108 [mln USD]

average flying hours in 1 year : 3000 [hours] technical life : 16 [year]

real average service life : 16 [years]

depreciation : 16 [years] to 10% residual value

financing interest per flying hour : 812 [EUR]

write off per flying hour : 1873 [EUR]

mean time between engine failure (MTBF) : 13782 [hr]

can continue fly on 3 engines, low risk for emergency landing for PUF

workhours per day : 11.55 [hr]

average flight hours till crash : 0.71 [mln hr] (237 service years)

safe flight hours till fatality : 16688 [hr] (5.6 service years)

Seat 5 + 9x6 = 54 + 10x4 = 40 + 7x first class = 106 passengers

reservation pax liability/flying hour : 7.72 [SDR*] (9.65 [eur])

insurance cost per hour : 700 [eur] insurance rate : 5.2 [%]

engine maintenance cost per hour : 150.5 [eur]

wing maintenance cost per hour : 268.8 [eur]

fuselage maintenance cost per hour : 206.32 [eur]

tire life (time till worn out) : 100 [cycles]

maintenance cost per hour (excluding engines): 1368 [eur]

direct operating cost per hour: 10226 [eur], DOC per km : 11.40 [eur]

DOC per seat 1000km flight (154 [pax] 2-class seating): 70.86 [eur/1000PK]

DOC per seat 1000km flight (high density seating): 69.74 [eur/1000PK]

DOC per kg cargo for a 1000km flight : 0.59 [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 : 4.55 [eur/pax]

airport landing fee / passenger : 4.55 [eur/pax]

retour ticket price 1000km trip : 223.01 [eur/pax]

price retour ticket Schiphol-Barcelona : 261.99 [eur/pax]

accidents with fatalities > see the accident file

Lufthansa Boeing 720-030B D-ABOH c/n 18057/190

notes : in case of PUF it had the lowest power-loading of all classic jetliners with 467 kg/KN.

Literature :

Boeing 720 - Wikipedia

Aircraft – Boeing 720B – Northwest Airlines History Center

Jane’s commercial transport aircraft page 51

Wat is dat voor een vliegtuig ? page 38

N724US | World Airline News

Straalverkeersvliegtuigen page 101

Praktisch handboek vliegtuigen deel 5 page 70,71

Jane’s all the world aircraft 1964-1965 page 189

Aircraft – Boeing 720B - Northwest Airlines History Center

Aircraft Performance Database > B720

Verkeersvliegtuigen (Moussault) page 83,152

www.aviation-safety.net

www.boeing-jets.ch

Verkehrsflugzeuge page 37

www.rzjets.net (productionlist)

https://contentzone.eurocontrol.int/aircraftperformance/default.aspx?

https://www.boeing.com/commercial/airports/plan-manuals

EL AL Fleet – Historic – Boeing 720B Aircraft | Israel Airline Museum

confidence rating regarding source data : medium - all information is only available from news, social media or unofficial sources

Pan American Boeing 720-023B N708PA c/n 18033 “jet clipper carib”, the engines are JT3D-1 turbofans, not the JT3C-7 as indicated above.

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 14 April 2025 contact : info.aircraftinvestigation@gmail.com ac jetpax 2020.py python 3.7.4