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weight and performance calculations for the Lockheed L-1649A Starliner
Lockheed L-1649A Starliner
role : non-stop trans-Atlantic airliner
importance : ****
first flight : 10 October 1956 at Burbank, California operational : June 1957
country : United States of America
design :
production : 43 aircraft
general information :
The L-1649 had an all-new wing with larger wingspan, but with a thinner
profile. It had integral fuel tanks extended to the wingtips, giving more
fuel capacity and longer range for more than 10.000 km.
So it could cross the Atlantic Ocean westward non-stop.
The inner engines were placed further outside and there was more than 400
kg extra sound-insulation applied. As a result, the sound in the
cabin was pleasantly low and the aircraft was therefore
popular with passengers. It was a competitor with the DC-7C, which had
already entered service on June 1, 1956.
The Starliner did not enter service with TWA until 1 June 1957
and was literally in between the DC-7C and the first jet
planes so Lockheed could only sell 43 Starliners.
Fuel capacity : 9600 US Gallons (36340 liters)
primary users : TWA, Air France, Lufthansa
flight crew : 6 cabin crew : 4 passengers : 92
flight crew consist of captain, first officer, reserve pilot, navigator and two
engineers
powerplant : 4 Wright R-3350-18EA2 Turbo Compound air-cooled 18 -cylinder radial
engine 1900 [hp](1416.8 KW) normal rating, supercharged engine, high blower,
constant power to height : 7400 [m] and with 3400 [hp](2535.4 KW) available for
take-off
dimensions :
wingspan : 45.72 [m], length : 35.41 [m], height : 7.54 [m]
wing area : 172.0 [m^2]
weights :
max.take-off weight : 70808 [kg]
empty weight operational : 41569 [kg] useful load : 12500 [kg]
performance :
maximum continuous speed : 607 [km/u] op 7400 [m]
normal cruise speed : 563 [km/u] op 5669 [m] (86 [%] power)
service ceiling : 7200 [m]
range with max fuel : 11062 [km] and allowance for 1211.9 [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 0015 tip : NACA 0011
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
7993 imp.gallon = 36336 liters fuel, enough for 7330 st. miles = 11794 km no-allowance range. MTOW 156.000 lb = 70762 kg
airscrew :
four Hamilton-Standard constant speed, reversible pitch 3 -bladed tractor airscrews with max. efficiency :0.85 [ ]
diameter airscrew 5.13 [m]
relative pitch (J) : 2.27 [ ]
power loading prop : 184.12 [KW/m]
high power loading prop > more bladed prop needed
theoretical pitch without slip : 12.92 [m]
blade angle prop at max.speed : 47.90 [ ]
tip-speed close to speed of sound (above Mach 0.85) > loose of efficiency
reduction : 0.35 [ ]
airscrew revs : 870 [r.p.m.]
aerodynamic pitch at max. continuous speed 11.63 [m]
blade-tip speed at max.continuous speed : 288 [m/s]
propellor noise in flight : 100 [Db]
calculation : *1* (dimensions)
measured wing chord : 3.75 [m] at 50% wingspan
mean wing chord : 3.76 [m]
calculated average wing chord tapered wing with rounded tips: 3.57 [m]
wing aspect ratio : 12.2 []
seize (span*length*height) : 12207 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 42.5 [kg/hr]
fuel consumption (econ. cruise speed) : 1194.5 [kg/hr] (1629.6 [litre/hr]) at 86 [%] power
distance flown for 1 kg fuel : 0.47 [km/kg] at 5669 [m] height, sfc : 245.0 [kg/kwh]
estimated total fuel capacity : 36341 [litre] (26638 [kg])
calculation : *3* (weight)
weight engine(s) dry with reduction gear : 6796.0 [kg] = 1.20 [kg/KW]
weight 1258.0 litre oil tank : 106.93 [kg]
oil tank filled with 42.5 litre oil : 38.2 [kg]
oil in engine 31.6 litre oil : 28.3 [kg]
fuel in engine 38.7 litre fuel : 28.34 [kg]
weight 692.8 litre gravity patrol tank(s) : 103.9 [kg]
weight jet stacks : 141.7 [kg]
weight NACA cowling 63.5 [kg]
weight variable pitch control : 63.2 [kg]
weight airscrew(s) incl. boss & bolts : 1579.6 [kg]
total weight propulsion system : 8886 [kg](12.6 [%])
***************************************************************
fuselage aluminium frame : 7572 [kg]
typical cabin layout for 92 passengers : pitch : 81 [cm] ( 3+2 ) seating in 18.0 rows
pax density (normal seating) : 0.80 [m2/pax]
high density seating passengers : 113 at 5 -abreast seating in 22.6 rows
weight 8 toilets : 61.1 [kg]
weight 7 hand fire extinguisher : 21 [kg]
weight pantry : 253.1 [kg]
weight 38 windows : 34.2 [kg]
weight 4 emergency exits : 12.0 [kg]
weight 5 life rafts : 115.0 [kg]
weight oxygen masks & oxygen generators : 59.8 [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. : 0.53 [m3]
cabin volume (usable), excluding flight deck : 169.22 [m3]
passenger cabin max.width : 3.28 [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 : 199.4 [kg]
weight air pressurization system : 43.3 [kg]
fuselage covering ( 258.0 [m2] duraluminium 3.96 [mm]) : 2690.3 [kg]
weight floor beams : 217.4 [kg]
weight cabin furbishing : 573.2 [kg]
weight cabin floor : 607.7 [kg]
fuselage (sound proof) isolation : 471.5 [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 Sperry Integrated Flight System : 11.0 [kg]
weight artificial horizon : 1.1 [kg]
weight instruments. : 38.0 [kg]
weight APU / engine starter: 70.8 [kg]
weight lighting : 23.0 [kg]
weight electricity generator : 23.0 [kg]
weight controls : 16.3 [kg]
weight seats : 510.0 [kg]
weight air conditioning : 138 [kg]
total weight fuselage : 13321 [kg](18.8 [%])
***************************************************************
total weight aluminium ribs (961 ribs) : 2525 [kg]
weight titanium firewalls and engine mounts : 201 [kg]
weight fuel tanks empty for total 35648 [litre] fuel : 2852 [kg]
weight wing covering (painted aluminium 4.89 [mm]) : 4545 [kg]
total weight aluminium spars (multi-cellular wing structure) : 2975 [kg]
weight wings : 10046 [kg]
weight wing/square meter : 58.41 [kg]
cantilever wing without bracing cables
weight rubber de-icing boots : 50.3 [kg]
weight fin & rudder (24.3 [m2]) : 1420.7 [kg]
weight stabilizer & elevator (19.4 [m2]): 1131.4 [kg]
weight flight control hydraulic servo actuators: 94.7 [kg]
weight fowler flaps (14.3 [m2]) : 424.6 [kg]
total weight wing surfaces & bracing : 16221 [kg] (22.9 [%])
*******************************************************************
wielen naar verhouding erg licht
wheel pressure : 17702.0 [kg]
weight 4 Dunlop main wheels (1330 [mm] by 266 [mm]) : 754.5 [kg]
weight 2 Dunlop nose wheels : 188.6 [kg]
weight hydraulic wheel-brakes : 54.1 [kg]
weight pneumatic-hydraulic shock absorbers : 72.1 [kg]
weight wheel hydraulic operated retraction system : 178.9 [kg]
weight undercarriage struts with axle 1535.2 [kg]
total weight landing gear : 2683.0 [kg] (3.8 [%]
*******************************************************************
********************************************************************
calculated empty weight : 41111 [kg](58.1 [%])
weight oil for 23.6 hours flying : 1002.2 [kg]
calculated operational weight empty : 42113 [kg] (59.5 [%])
published operational weight empty : 41569 [kg] (58.7 [%])
weight crew : 810 [kg]
weight fuel for 2.0 hours flying : 2389 [kg]
weight catering : 632.7 [kg]
weight water : 506.1 [kg]
********************************************************************
operational weight empty: 46451 [kg](65.6 [%])
weight 92 passengers : 7084 [kg]
weight luggage : 1122 [kg]
weight cargo : 4294 [kg]
operational weight loaded: 58951 [kg](83.3 [%])
fuel reserve : 11857.2 [kg] enough for 9.93 [hours] flying
operational weight fully loaded : 70808 [kg] with fuel tank filled for 53 [%]
published maximum take-off weight : 70808 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 6.98 [kg/kW]
power loading (operational without useful load) : 8.20 [kg/kW]
power loading (Take-off) 1 PUF: 9.31 [kg/kW]
max.total take-off power : 10141.5 [kW]
calculation : *5* (loads)
manoeuvre load : 3.7 [g] at 1000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.1 [g]
design flight time : 13.75 [hours]
design cycles : 2411 sorties, design hours : 33163 [hours]
operational wing loading : 3647 [N/m^2]
wing stress (3 g) during operation : 187 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.70 ["]
max. angle of attack (stalling angle, clean) : 11.54 ["]
max. angle of attack (full flaps) : 10.65 ["]
angle of attack at max. speed : 1.82 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.16 [ ]
lift coefficient at max. speed : 0.33 [ ]
lift coefficient at max. angle of attack : 1.24 [ ]
max.lift coefficient full flaps : 1.67 [ ]
induced drag coefficient at max.speed : 0.0036 [ ]
drag coefficient at max. speed : 0.0192 [ ]
drag coefficient (zero lift) : 0.0156 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 69614 [kg]): 260 [km/u]
stalling speed at sea-level with full flaps (normal landing weight): 170 [km/u]
landing speed at sea-level (normal landing weight : 57124 [kg]): 195 [km/hr]
max. rate of climb speed : 264 [km/hr] at sea-level
max. endurance speed : 249 [km/u] min.fuel/hr : 593 [kg/hr] at height : 610 [m]
max. range speed : 435 [km/u] min. fuel consumption : 2.065 [kg/km] at cruise height : 6096 [m]
cruising speed : 563 [km/hr] at 5669 [m] (power:95 [%])
max. continuous speed* : 607.00 [km/hr] at 7400 [m] (power:100 [%])
climbing speed at sea-level (loaded) : 281 [m/min]
climbing speed at 1000 [m] with 1 engine out (PUF / MTOW) : 297 [m/min]
climbing speed at 1000 [m] with 2 engines out (2xPUF / MTOW) : 99 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 314.6 [km/u]
emergency/TO power : 3400 [hp] at 2900 [rpm]
static prop wash : 175 [km/u]
high wheel pressure, can only take off from paved runways
take-off distance at sea-level concrete runway : 1768 [m]
take-off distance at sea-level over 15 [m] height : 2003 [m]
landing run : 843 [m]
landing run from 15 [m] : 1618 [m]
lift/drag ratio : 21.97 [ ]
climb to 1000m with max payload : 5.97 [min]
climb to 2000m with max payload : 12.39 [min]
climb to 3000m with max payload : 19.36 [min]
climb to 5000 [m] with max payload : 36.88 [min]
practical ceiling (operational weight empty 46451 [kg] ) : 10500 [m]
practical ceiling fully loaded (mtow- 30 min.fuel:70211 [kg] ) : 8000 [m]
calculation *10* (action radius & endurance)
published range : 11062 [km] with 10 crew and 4415.2 [kg] useful load and 88.1 [%] fuel (no reserves)
range : 7251 [km] with 10 crew and 12500.0 [kg] useful load and 57.8 [%] fuel
range : 9275 [km] with 92.0 passengers with each 12.2 [kg] luggage and 73.9 [%] fuel
Available Seat Kilometres (ASK) : 853310 [paskm]
max range theoretically with additional fuel tanks total 39036.8 [litre] fuel : 13853 [km]
useful load with range 500km : 27553 [kg]
useful load with range 500km : 92 passengers
production (theor.max load): 15512 [tonkm/hour]
production (useful load): 7038 [tonkm/hour]
production (passengers): 51796 [paskm/hour]
combi aircraft mail/freight/passengers
oil and fuel consumption per tonkm : 0.080 [kg]
fuel cost per paskm : 0.024 [eur]
crew cost per paskm : 0.026 [eur]
economic hours : 18250 [hours] is less then design hours
time between engine failure : 5671 [hr]
can continue fly on 3 engines, low risk for emergency landing for PUF
writing off per paskm : 0.036 [eur]
insurance per paskm : 0.0000 [eur]
maintenance cost per paskm : 0.189 [eur]
direct operating cost per paskm : 0.275 [eur]
direct operating cost per tonkm (max. load): 0.920 [eur]
direct operating cost per tonkm (normal useful load): 2.027 [eur]
Literature :
piston engined airliners page 58
prakt. handb. vliegt. deel 5 page 48
verkeersvliegtuigen Moussault page 122
Amerikaanse vliegtuig bouwers page 108
10 October 1956: Lockheed L-1649 Starliner - This Day in Aviation
* 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
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