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weight and performance calculations for the Lockheed L-1049G Super Constellation

Lockheed L-1049G Super Constellation

role : long-range airliner

importance : ****

first flight : 7 December 1954 operational : July 1955

country : United States of America

design :

production : 99 aircraft

general information :

After the L-1049E followed the L-1049F, a military version with designation C-121G.

The L-1049G had more powerful engines and optional

tip tanks with a capacity of 2273 litres. Total fuel : 29337 litres

They were equipped with a Bendix or RCA weather radar in the nose, giving a 70cm longer nose.

KLM received its first L-1049G in December 1955.

They flew on the route Amsterdam - New York, and now non-stop for the first time

16 hours to NY against the prevailing winds and back in 14 hours.

primary users : KLM

flight crew : 4 cabin crew : 4 passengers : 66-95

flight crew consist of pilot, co-pilot, radio operator and engineer

powerplant : 4 Wright R-3350-18DA3 Turbo Compound air-cooled 18 -cylinder radial engine 1700 [hp](1267.7 KW)

normal rating, supercharged engine, high blower, constant power to height : 7400 [m]

and with 3250 [hp](2423.5 KW) available for take-off

dimensions :

wingspan : 37.62 [m], length : 35.41 [m], height : 7.55 [m]

wing area : 154.4 [m^2]

weights :

max.take-off weight : 62372 [kg]

empty weight operational : 33119 [kg] useful load : 11974 [kg]

performance :

maximum continuous speed : 589 [km/u] op 7400 [m]

normal cruise speed : 533 [km/u] op 6100 [m] (82 [%] power)

service ceiling : 7620 [m]

range with max fuel : 9810 [km] and allowance for 1057.9 [km] diversion and 30 [min] hold

description :

low-winged monoplane with retractable landing gear with nose wheel

tapered multi-cellular wing with flush-riveted stressed skin

with Fowler flaps airfoil : NACA

engines and landing gear attached to the wings, fuel tanks in the wings

construction : all-metal aluminium-alloy stressed-skin construction with pressurized

fuselage fuselage shape : O

airscrew :

four Hamilton-Standard constant speed, reversible pitch 3 -bladed tractor airscrews with max. efficiency :0.84 [ ]

diameter airscrew 4.60 [m]

relative pitch (J) : 2.03 [ ]

power loading prop : 183.72 [KW/m]

high power loading prop > more bladed prop needed

theoretical pitch without slip : 10.39 [m]

blade angle prop at max.speed : 44.78 [ ]

tip-speed close to speed of sound (above Mach 0.85) > loose of efficiency

reduction : 0.44 [ ]

airscrew revs : 1050 [r.p.m.]

aerodynamic pitch at max. continuous speed 9.35 [m]

blade-tip speed at max.continuous speed : 301 [m/s]

propellor noise in flight : 104 [Db]

calculation : *1* (dimensions)

measured wing chord : 4.10 [m] at 50% wingspan

mean wing chord : 4.10 [m]

calculated average wing chord tapered wing with rounded tips: 4.00 [m]

wing aspect ratio : 9.2 []

seize (span*length*height) : 10058 [m^3]

calculation : *2* (fuel consumption)

oil consumption : 40.6 [kg/hr]

fuel consumption (econ. cruise speed) : 1029.8 [kg/hr] (1404.9 [litre/hr]) at 82 [%]

power

distance flown for 1 kg fuel : 0.52 [km/kg] at 6100 [m] height, sfc : 248.0 [kg/kwh]

estimated total fuel capacity : 29348 [litre] (21512 [kg])

calculation : *3* (weight)

weight engine(s) dry with reduction gear : 6000.0 [kg] = 1.18 [kg/KW]

weight 1124.8 litre oil tank : 95.61 [kg]

oil tank filled with 38.0 litre oil : 34.1 [kg]

oil in engine 28.2 litre oil : 25.4 [kg]

fuel in engine 34.6 litre fuel : 25.35 [kg]

weight 597.3 litre gravity patrol tank(s) : 89.6 [kg]

weight jet stacks : 126.8 [kg]

weight NACA cowling 56.8 [kg]

weight variable pitch control : 47.3 [kg]

weight airscrew(s) incl. boss & bolts : 1183.6 [kg]

total weight propulsion system : 7637 [kg](12.2 [%])

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

fuselage aluminium frame : 6808 [kg]

typical cabin layout for 85 passengers : pitch : 81 [cm] ( 3+2 ) seating in 17.0 rows

pax density (normal seating) : 0.87 [m2/pax]

high density seating passengers : 113 at 5 -abreast seating in 22.6 rows

weight 6 toilets : 50.0 [kg]

weight 7 hand fire extinguisher : 20 [kg]

weight pantry : 219.0 [kg]

weight 36 windows : 32.4 [kg]

weight 4 emergency exits : 12.0 [kg]

weight 4 life rafts : 106.2 [kg]

weight oxygen masks & oxygen generators : 55.2 [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]

extra main deck space for freight/mail/luggage etc. : 8.60 [m3]

cabin volume (usable), excluding flight deck : 170.32 [m3]

passenger cabin max.width : 3.29 [m] cabin length : 22.35 [m] cabin height : 2.36 [m]

pressure at cruise height 6100.00 [m] : 0.47 [kg/cm2] cabin pressure : 0.86 [kg/cm2]

weight rear pressure bulkhead : 180.7 [kg]

weight air pressurization system : 43.4 [kg]

fuselage covering ( 258.0 [m2] duraluminium 3.56 [mm]) : 2425.2 [kg]

weight floor beams : 223.7 [kg]

weight cabin furbishing : 521.4 [kg]

weight cabin floor : 550.8 [kg]

fuselage (sound proof) isolation : 119.3 [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 artificial horizon : 1.1 [kg]

weight instruments. : 38.0 [kg]

weight APU / engine starter: 63.4 [kg]

weight lighting : 21.2 [kg]

weight electricity generator : 21.2 [kg]

weight controls : 15.2 [kg]

weight seats : 465.0 [kg]

weight air conditioning : 128 [kg]

total weight fuselage : 12044 [kg](19.3 [%])

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

total weight aluminium ribs (776 ribs) : 2224 [kg]

weight titanium firewalls and engine mounts : 180 [kg]

weight fuel tanks empty for total 28751 [litre] fuel : 2300 [kg]

weight wing covering (painted aluminium 2.44 [mm]) : 2037 [kg]

total weight aluminium spars (multi-cellular wing structure) : 2286 [kg]

weight wings : 6547 [kg]

weight wing/square meter : 42.40 [kg]

cantilever wing without bracing cables

weight rubber de-icing boots : 41.4 [kg]

weight fin & rudder (16.4 [m2]) : 699.0 [kg]

weight stabilizer & elevator (17.4 [m2]): 737.7 [kg]

weight flight control hydraulic servo actuators: 46.6 [kg]

weight fowler flaps (12.9 [m2]) : 278.8 [kg]

total weight wing surfaces & bracing : 10830 [kg] (17.4 [%])

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

wielen naar verhouding erg licht

wheel pressure : 15593.0 [kg]

weight 4 Dunlop main wheels (1330 [mm] by 266 [mm]) : 689.6 [kg]

weight 2 Dunlop nose wheels : 172.4 [kg]

weight hydraulic wheel-brakes : 45.1 [kg]

weight pneumatic-hydraulic shock absorbers : 60.1 [kg]

weight wheel hydraulic operated retraction system : 160.5 [kg]

weight undercarriage struts with axle 1372.7 [kg]

total weight landing gear : 2407.4 [kg] (3.9 [%]

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

Flight deck of L-1049G VH-EAG

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

calculated empty weight : 32918 [kg](52.8 [%])

weight oil for 22.1 hours flying : 896.0 [kg]

calculated operational weight empty : 33814 [kg] (54.2 [%])

published operational weight empty : 33119 [kg] (53.1 [%])

weight crew : 648 [kg]

weight fuel for 2.0 hours flying : 2060 [kg]

weight catering : 547.6 [kg]

weight water : 438.0 [kg]

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

operational weight empty: 37508 [kg](60.1 [%])

weight 85 passengers : 6545 [kg]

weight luggage : 1037 [kg]

weight cargo : 4392 [kg]

operational weight loaded: 49482 [kg](79.3 [%])

fuel reserve : 12890.4 [kg] enough for 12.52 [hours] flying

operational weight fully loaded : 62372 [kg] with fuel tank filled for 69 [%]

published maximum take-off weight : 62372 [kg] (100.0 [%])

calculation : * 4 * (engine power)

power loading (Take-off) : 6.43 [kg/kW]

power loading (operational without useful load) : 7.40 [kg/kW]

power loading (Take-off) 1 PUF: 8.58 [kg/kW]

max.total take-off power : 9694.1 [kW]

calculation : *5* (loads)

manoeuvre load : 4.1 [g] at 1000 [m]

limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.1 [g]

design flight time : 12.88 [hours]

design cycles : 2479 sorties, design hours : 31944 [hours]

operational wing loading : 3502 [N/m^2]

wing stress (3 g) during operation : 248 [N/kg] at 3g emergency manoeuvre

calculation : *6* (angles of attack)

angle of attack zero lift : -1.80 ["]

max. angle of attack (stalling angle, clean) : 12.97 ["]

max. angle of attack (full flaps) : 12.08 ["]

angle of attack at max. speed : 1.76 ["]

calculation : *7* (lift & drag ratios

lift coefficient at angle of attack 0° : 0.16 [ ]

lift coefficient at max. speed : 0.32 [ ]

lift coefficient at max. angle of attack : 1.31 [ ]

max.lift coefficient full flaps : 1.74 [ ]

induced drag coefficient at max.speed : 0.0045 [ ]

drag coefficient at max. speed : 0.0204 [ ]

drag coefficient (zero lift) : 0.0158 [ ]

calculation : *8* (speeds

stalling speed at sea-level (OW loaded : 61342 [kg]): 251 [km/u]

stalling speed at sea-level with full flaps (normal landing weight): 161 [km/u]

landing speed at sea-level (normal landing weight : 47904 [kg]): 185 [km/hr]

max. rate of climb speed : 255 [km/hr] at sea-level

max. endurance speed : 267 [km/u] min.fuel/hr : 687 [kg/hr] at height : 610 [m]

max. range speed : 476 [km/u] min. fuel consumption : 2.221 [kg/km] at cruise height :

6401 [m]

cruising speed : 533 [km/hr] at 6100 [m] (power:89 [%])

max. continuous speed* : 589.00 [km/hr] at 7400 [m] (power:100 [%])

climbing speed at sea-level (loaded) : 264 [m/min]

climbing speed at 1000 [m] with 1 engine out (PUF / MTOW) : 275 [m/min]

climbing speed at 1000 [m] with 2 engines out (2xPUF / MTOW) : 59 [m/min]

calculation : *9* (regarding various performances)

take-off speed : 303.4 [km/u]

emergency/TO power : 3250 [hp] at 2800 [rpm]

static prop wash : 187 [km/u]

high wheel pressure, can only take off from paved runways

take-off distance at sea-level concrete runway : 1525 [m]

take-off distance at sea-level over 15 [m] height : 1766 [m]

landing run : 731 [m]

landing run from 15 [m] : 1465 [m]

lift/drag ratio : 18.69 [ ]

climb to 1000m with max payload : 9.19 [min]

climb to 2000m with max payload : 19.77 [min]

climb to 3000m with max payload : 32.38 [min]

climb to 5000 [m] with max payload : 78.31 [min]

practical ceiling (operational weight empty 37508 [kg] ) : 10200 [m]

practical ceiling fully loaded (mtow- 30 min.fuel:61857 [kg] ) : 5700 [m]

calculation *10* (action radius & endurance)

published range : 9810 [km] with 8 crew and 8956.0 [kg] useful load and 88.1 [%] fuel

(no reserves)

range : 8248 [km] with 8 crew and 11974.0 [kg] useful load and 74.1 [%] fuel

range : 10521 [km] with 85.0 passengers with each 12.2 [kg] luggage and 94.5 [%]

fuel

Available Seat Kilometres (ASK) : 894299 [paskm]

max range theoretically with additional fuel tanks total 38849.3 [litre] fuel : 12819

[km]

useful load with range 500km : 27511 [kg]

useful load with range 500km : 85 passengers

production (theor.max load): 14663 [tonkm/hour]

production (useful load): 6382 [tonkm/hour]

production (passengers): 45305 [paskm/hour]

combi aircraft mail/freight/passengers

oil and fuel consumption per tonkm : 0.073 [kg]

fuel cost per paskm : 0.024 [eur]

crew cost per paskm : 0.023 [eur]

economic hours : 18250 [hours] is less then design hours

time between engine failure : 2106 [hr]

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

writing off per paskm : 0.033 [eur]

insurance per paskm : 0.0001 [eur]

maintenance cost per paskm : 0.188 [eur]

direct operating cost per paskm : 0.268 [eur]

direct operating cost per tonkm (max. load): 0.827 [eur]

direct operating cost per tonkm (normal useful load): 1.900 [eur]

literature :

piston engined airliners page 56,58

luchtvaart jan'87 page 26 t/m 31

praktisch handboek vliegtuigen deel 5 page 48

verkeersvliegtuigen Moussault page

* max. continuous speed : max. level speed maintainable for minimal 30 min.

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 03 April 2022 contact : info.aircraftinvestigation@gmail.com python 3.7.4