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weight and performance calculations for the Lockheed L-1049 Super Constellation
Lockheed L-1049 Super Constellation
role : long range airliner
importance : ****
first flight : 13 October 1950 operational : December 1951
country : United States of America
design :
production : 24 aircraft
general information :
Lockheed developed a larger and more powerful version of the Constellation in response to the arrival of the larger and pressurized Douglas DC-6 airliner.
The fuselage was extended by 5.62m, so that there was now room for 69 to 92 passengers. The cockpit was complete renewed and the cabin got larger square windows.
It received Wright R-3350-C18-CA1 engines of 2800 hp (2089 KW) with jet stacks for additional thrust.
The fuel capacity was increased to 24794 liters (6550 US Gallon)
In October 1950 it made its first flight and at 15 December 1951 it entered service with Eastern Air Lines.
It was a little underpowered and it was outperformed by its main rival the Douglas DC-6B.
A completely new electrical system was designed and built, including a new electro-pneumatic de-icing system. This new system electrically heated the leading edge of the aerodynamic surfaces, while inflatable pneumatic cylinders covered the remainder of the leading edge to 10% of the aerodynamic chord. Additional luggage hatches and a cargo door were also offered for installation.
Also there was paid attention again to the supercharging, heating and ventilation systems, which were again improved. Now at an altitude of 20,000 feet (6096m)in the cabin, it was possible to maintain a pressure corresponding to an altitude of 5,000 feet (1524m).
Users : Eastern Air Lines (10), TWA (14)
flight crew : 4 cabin crew : 4 passengers : 80
flight crew consist of pilot, co-pilot, radio operator and engineer
powerplant : 4 Wright R-3350-C18-CA1 Duplex-Cyclone air-cooled 18 -cylinder radial
engine 2150 [hp](1603.3 KW) normal rating, supercharged engine, high blower,
constant power to height : 4260 [m] and with 2800 [hp](2088.0 KW) available for
take-off
dimensions :
wingspan : 37.49 [m], length : 34.62 [m], height : 7.54 [m]
wing area : 153.0 [m^2]
weights :
max.take-off weight : 54432 [kg]
empty weight operational : 31298 [kg] useful load : 9200 [kg]
performance :
maximum continuous speed : 575 [km/u] op 4260 [m]
normal cruise speed : 515 [km/u] op 6100 [m] (67 [%] power)
service ceiling : 7800 [m]
range with max fuel : 6707 [km] and allowance for 647.9 [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 : root NACA 23018 tip NACA 4412
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 :0.83 [ ]
diameter airscrew 4.62 [m]
relative pitch (J) : 1.96 [ ]
power loading prop : 231.35 [KW/m]
N6206C c/n 4006
theoretical pitch without slip : 10.06 [m]
blade angle prop at max.speed : 43.75 [ ]
tip-speed close to speed of sound (above Mach 0.85) > loose of efficiency
reduction : 0.44 [ ]
airscrew revs : 1059 [r.p.m.]
aerodynamic pitch at max. continuous speed 9.05 [m]
blade-tip speed at max.continuous speed : 302 [m/s]
propellor noise in flight : 104 [Db]
calculation : *1* (dimensions)
measured wing chord : 3.96 [m] at 50% wingspan
mean wing chord : 4.08 [m]
calculated average wing chord tapered wing with rounded tips: 3.98 [m]
wing aspect ratio : 9.2 []
seize (span*length*height) : 9786 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 51.3 [kg/hr]
fuel consumption (econ. cruise speed) : 1229.6 [kg/hr] (1677.4 [litre/hr]) at 67 [%] power
distance flown for 1 kg fuel : 0.42 [km/kg] at 6100 [m] height, sfc : 286.0 [kg/kwh]
estimated total fuel capacity : 24795 [litre] (18175 [kg])
calculation : *3* (weight)
weight engine(s) dry with reduction gear : 5288.0 [kg] = 0.82 [kg/KW]
weight 1053.4 litre oil tank : 89.54 [kg]
oil tank filled with 48.1 litre oil : 43.2 [kg]
oil in engine 35.7 litre oil : 32.1 [kg]
fuel in engine 43.7 litre fuel : 32.07 [kg]
N6203C c/n 4003 L-1049
weight 713.1 litre gravity patrol tank(s) : 107.0 [kg]
weight jet stacks : 160.3 [kg]
weight NACA cowling 71.8 [kg]
weight variable pitch control : 54.2 [kg]
weight airscrew(s) incl. boss & bolts : 1354.1 [kg]
total weight propulsion system : 7178 [kg](13.2 [%])
***************************************************************
fuselage aluminium frame : 6592 [kg]
typical cabin layout for 80 passengers : pitch : 81 [cm] ( 3+2 ) seating in 16.0 rows
pax density (normal seating) : 0.89 [m2/pax]
high density seating passengers : 110 at 5 -abreast seating in 21.9 rows
weight 4 toilets : 32.2 [kg]
weight 6 hand fire extinguisher : 18 [kg]
weight pantry : 145.9 [kg]
weight 34 windows : 30.6 [kg]
weight 4 emergency exits : 12.0 [kg]
weight 4 life rafts : 100.0 [kg]
weight oxygen masks & oxygen generators : 52.0 [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. : 14.27 [m3]
cabin volume (usable), excluding flight deck : 165.02 [m3]
Eastern airlines N6232G
passenger cabin max.width : 3.30 [m] cabin length : 21.64 [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 : 179.6 [kg]
weight air pressurization system : 42.1 [kg]
fuselage covering ( 251.4 [m2] duraluminium 3.54 [mm]) : 2350.2 [kg]
weight floor beams : 230.5 [kg]
weight cabin furbishing : 462.2 [kg]
weight cabin floor : 487.6 [kg]
fuselage (sound proof) isolation : 117.1 [kg]
weight radio transceiver equipment : 7.0 [kg]
weight radio direction finding (RDF) equipment : 5.0 [kg]
weight artificial horizon : 1.1 [kg]
weight instruments. : 13.0 [kg]
weight APU / engine starter: 80.2 [kg]
weight lighting : 20.0 [kg]
weight electricity generator : 20.0 [kg]
weight controls : 15.0 [kg]
weight seats : 440.0 [kg]
weight air conditioning : 120 [kg]
total weight fuselage : 11489 [kg](21.1 [%])
***************************************************************
total weight aluminium ribs (681 ribs) : 1941 [kg]
weight engine mounts : 321 [kg]
weight fuel tanks empty for total 24082 [litre] fuel : 1927 [kg]
weight wing covering (painted aluminium 2.44 [mm]) : 2014 [kg]
total weight aluminium spars (multi-cellular wing structure) : 2253 [kg]
weight wings : 6208 [kg]
weight wing/square meter : 40.58 [kg]
cantilever wing without bracing cables
weight rubber de-icing boots : 41.2 [kg]
weight fin & rudder (16.3 [m2]) : 664.4 [kg]
weight stabilizer & elevator (17.2 [m2]): 699.6 [kg]
weight flight control hydraulic servo actuators: 44.3 [kg]
weight fowler flaps (12.8 [m2]) : 264.7 [kg]
total weight wing surfaces & bracing : 10170 [kg] (18.7 [%])
*******************************************************************
wheel pressure : 13608.0 [kg]
weight 4 Dunlop main wheels (1330 [mm] by 266 [mm]) : 744.6 [kg]
weight nose wheel : 93.1 [kg]
weight hydraulic wheel-brakes : 40.5 [kg]
weight pneumatic-hydraulic shock absorbers : 54.0 [kg]
weight wheel hydraulic operated retraction system : 155.8 [kg]
weight undercarriage struts with axle 1263.4 [kg]
total weight landing gear : 2337.0 [kg] (4.3 [%]
*******************************************************************
********************************************************************
calculated empty weight : 31174 [kg](57.3 [%])
weight oil for 15.6 hours flying : 801.8 [kg]
calculated operational weight empty : 31975 [kg] (58.7 [%])
published operational weight empty : 31298 [kg] (57.5 [%])
weight crew : 648 [kg]
weight fuel for 2.0 hours flying : 2459 [kg]
weight catering : 364.7 [kg]
weight water : 291.7 [kg]
********************************************************************
operational weight empty: 35739 [kg](65.7 [%])
weight 80 passengers : 6160 [kg]
weight luggage : 976 [kg]
weight cargo : 2064 [kg]
operational weight loaded: 44939 [kg](82.6 [%])
fuel reserve : 9493.2 [kg] enough for 7.72 [hours] flying
operational weight fully loaded : 54432 [kg] with fuel tank filled for 66 [%]
published maximum take-off weight : 54432 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 6.52 [kg/kW]
power loading (operational without useful load) : 5.57 [kg/kW]
power loading (Take-off) 1 PUF: 8.69 [kg/kW]
max.total take-off power : 8351.8 [kW]
calculation : *5* (loads)
manoeuvre load : 4.3 [g] at 1000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.3 [g]
design flight time : 9.12 [hours]
design cycles : 3443 sorties, design hours : 31385 [hours]
operational wing loading : 3134 [N/m^2]
wing stress (3 g) during operation : 232 [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) : 12.96 ["]
max. angle of attack (full flaps) : 12.07 ["]
angle of attack at max. speed : 0.74 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.16 [ ]
lift coefficient at max. speed : 0.23 [ ]
lift coefficient at max. angle of attack : 1.31 [ ]
max.lift coefficient full flaps : 1.74 [ ]
induced drag coefficient at max.speed : 0.0023 [ ]
drag coefficient at max. speed : 0.0204 [ ]
drag coefficient (zero lift) : 0.0181 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 53202 [kg]): 235 [km/u]
stalling speed at sea-level with full flaps (normal landing weight): 154 [km/u]
landing speed at sea-level (normal landing weight : 43345 [kg]): 177 [km/hr]
max. rate of climb speed : 238 [km/hr] at sea-level
max. endurance speed : 244 [km/u] min.fuel/hr : 686 [kg/hr] at height : 610 [m]
max. range speed : 434 [km/u] min. fuel consumption : 2.436 [kg/km] at cruise height :
6401 [m]
cruising speed : 515 [km/hr] at 6100 [m] (power:71 [%])
max. continuous speed* : 575.00 [km/hr] at 4260 [m] (power:100 [%])
climbing speed at sea-level (loaded) : 464 [m/min]
climbing speed at 1000 [m] with 1 engine out (PUF / MTOW) : 269 [m/min]
climbing speed at 1000 [m] with 2 engines out (2xPUF / MTOW) : 60 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 284.7 [km/u]
emergency/TO power : 2800 [hp] at 2800 [rpm]
static prop wash : 188 [km/u]
high wheel pressure, can only take off from paved runways
take-off distance at sea-level concrete runway : 1199 [m]
take-off distance at sea-level over 15 [m] height : 1327 [m]
landing run : 667 [m]
landing run from 15 [m] : 1368 [m]
lift/drag ratio : 17.52 [ ]
climb to 1000m with max payload : 3.36 [min]
climb to 2000m with max payload : 6.89 [min]
climb to 3000m with max payload : 10.62 [min]
climb to 5000 [m] with max payload : 22.34 [min]
practical ceiling (operational weight empty 35739 [kg] ) : 9000 [m]
practical ceiling fully loaded (mtow- 30 min.fuel:53817 [kg] ) : 6500 [m]
calculation *10* (action radius & endurance)
published range : 6707 [km] with 8 crew and 5795.8 [kg] useful load and 88.1 [%] fuel
(no reserves)
range : 5281 [km] with 8 crew and 9200.0 [kg] useful load and 69.4 [%] fuel
range : 6146 [km] with 80.0 passengers with each 12.2 [kg] luggage and 80.7 [%] fuel
Available Seat Kilometres (ASK) : 491654 [paskm]
max range theoretically with additional fuel tanks total 30526.2 [litre] fuel : 9186 [km]
useful load with range 500km : 21182 [kg]
useful load with range 500km : 80 passengers
production (theor.max load): 10909 [tonkm/hour]
production (useful load): 4738 [tonkm/hour]
production (passengers): 41200 [paskm/hour]
combi aircraft mail/freight/passengers
oil and fuel consumption per tonkm : 0.117 [kg]
fuel cost per paskm : 0.031 [eur]
crew cost per paskm : 0.025 [eur]
economic hours : 18250 [hours] is less then design hours
time between engine failure : 1762 [hr]
can continue fly on 3 engines, low risk for emergency landing for PUF
writing off per paskm : 0.034 [eur]
insurance per paskm : 0.0002 [eur]
maintenance cost per paskm : 0.162 [eur]
direct operating cost per paskm : 0.254 [eur]
direct operating cost per tonkm (max. load): 0.958 [eur]
direct operating cost per tonkm (normal useful load): 2.205 [eur]
Literature :
praktisch handboek vliegtuigen deel 5 page 47
piston-engined airliners page 58
verkeersvliegtuigen Moussault page 121
Construction List - L-1049 - PlaneLogger
Amerikaanse vliegtuigbouwers page 107
Lockheed L-1049 Super Constellation (airwar.ru)
* 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