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weight and performance calculations for the Junkers Ju 52/3mce
Junkers Ju 52/3mce
role : multi-engined passenger aircraft
importance : *****
first flight : Ju 52/3m : 7 March 1932 operational : May 1932
country : Germany
design : Ernst Zindel
nick name : “Tante Ju”
production : 200 civil aircraft 4600 military aircraft
general information :
Was widely used before WWII as passenger aircraft and became even more successful as military transport, being used in the Spanish civil war and later in WWII.
First 3-engined production aircraft had 660 hp BMW 132A-1 engines.
users : Lufthansa, Luftwaffe
crew : 3 passengers : 17
engine : 3 BMW 132A-3 air-cooled 9 -cylinder radial engine 690 [hp](514.5 KW) max.30 min 2250 rpm at sea level, 525 [hp] max.duration at sea level
supercharged engine, critical height : 500 [m]
dimensions :
wingspan : 29.25 [m], length : 18.9 [m], height : 5.54[m]
wing area : 110.5 [m^2]
weights :
max.take-off weight : 9500 [kg]
empty weight operational : 5720 [kg] useful load : 1700 [kg]
performance :
maximum speed :277 [km/u] op 910 [m]
cruise speed :249 [km/u] op 910 [m]
service ceiling : 5200 [m]
range : 1280 [km] with 17 passengers
description :
low-winged monoplane with fixed landing gear with tail wheel
multi spar tapered wing with slotted flaps/ailerons
2 engines attached to the wings 1 in the fuselage, landing gear attached to the wings, useful load inside the fuselage, fuel tanks in the wings
construction :all-metal (duraluminium) airplane
airscrew :
ground adjustable 2 -bladed metal Hamilton Standard tractor propeller with max. efficiency :0.72 [ ]
estimated diameter airscrew 3.26 [m]
power loading prop : 157.83 [KW/m]
prop efficiency ratio: 15.20 [1/s]
angle of attack prop : 23.31 [ ]
reduction : 0.62 [ ]
airscrew revs : 1395 [r.p.m.]
pitch at Max speed 3.31 [m]
blade-tip speed at Vmax and max revs. : 250 [m/s]
calculation : *1* (dimensions)
measured wing chord : 4.11 [m] at 50% wingspan
mean wing chord : 3.78 [m]
calculated average wing chord tapered wing with rounded tips: 4.26 [m]
wing aspect ratio : 7.74 []
seize (span*length*height) : 3063 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 24.7 [kg/hr]
fuel consumption(cruise speed) : 315.0 [kg/hr] (429.8 [litre/hr]) at 67 [%] power
distance flown for 1 kg fuel : 0.79 [km/kg] at 2600 [m] height, sfc : 304.2 [kg/kwh]
estimated total fuel capacity : 1788 [litre] (1311 [kg])
calculation : *3* (weight)
weight engine(s) dry : 1512.0 [kg] = 0.98 [kg/KW]
weight reduction gear : 61.7 [kg]
weight 159.6 litre oil tank : 13.57 [kg]
oil tank filled with 11.6 litre oil : 10.4 [kg]
oil in engine 8.6 litre oil : 7.7 [kg]
fuel in engine 10.5 litre fuel : 7.72 [kg]
weight 182.7 litre gravity patrol tank(s) : 27.4 [kg]
weight gas starter : 12.6 [kg]
weight cowling (Townend ring) 20.6 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 148.5 [kg]
total weight propulsion system : 1870 [kg](19.7 [%])
***************************************************************
fuselage aluminium frame : 981 [kg]
cabin layout : pitch : 87 [cm] (1+1) seating in 8.5 rows
weight toilet : 8 [kg]
weight 2 fire extinguisher : 6 [kg]
weight pantry : 10.0 [kg]
weight 17.0 windows : 15.30 [kg]
passenger cabin width : 1.68 [m] cabin length : 7.99 [m] cabin height : 1.90 [m]
cabin length / length : 42.3 [%]
weight cabin furbishing : 58.68 [kg]
weight cabin floor : 85.84 [kg]
fuselage covering ( 67.5 [m2] duraluminium 0.75 [mm]) : 131.0 [kg]
weight radio navigation equipment : 7.0 [kg]
weight instruments. : 4.0 [kg]
weight APU : 50 [kg]
weight lighting : 4.2 [kg]
weight controls : 9.8 [kg]
weight seats : 100.0 [kg]
weight air conditioning : 26 [kg]
weight engine mount and firewall : 26 [kg]
total weight fuselage : 1522 [kg](16.0 [%])
***************************************************************
weight wing covering (painted aluminium 0.75 mm) : 448 [kg]
total weight aluminium ribs (128 ribs) : 339 [kg]
weight engine mounts : 51 [kg]
weight fuel tanks empty for total 1606 [litre] fuel : 128 [kg]
load on front upper spar (clmax) per running metre : 2447.6 [N]
load on rear upper spar (vmax) per running metre : 933.5 [N]
total weight 4 aluminium spars : 532 [kg]
weight wings : 1318 [kg]
weight wing/square meter : 11.93 [kg]
cantilever wing without bracing cables
weight fin & rudder (9.9 [m2]) : 119.9 [kg]
weight stabilizer & elevator (12.4 [m2]): 149.1 [kg]
total weight wing surfaces & bracing : 1767 [kg] (18.6 [%])
*******************************************************************
wheel pressure : 4750.0 [kg]
weight 2 wheels (1360 [mm] by 227 [mm]) : 239.2 [kg]
weight tailwheel(s) : 5.9 [kg]
weight undercarriage with axle 288.9 [kg]
total weight landing gear : 534.1 [kg] (5.6 [%]
*******************************************************************
********************************************************************
calculated empty weight : 5694 [kg](59.9 [%])
weight oil for 4.4 hours flying : 108.7 [kg]
calculated operational weight empty : 5803 [kg] (61.1 [%])
published operational weight empty : 5720 [kg] (60.2 [%])
weight crew : 243 [kg]
weight fuel for 2.0 hours flying : 630 [kg]
********************************************************************
operational weight empty: 6676 [kg](70.3 [%])
weight 17 passengers : 1309 [kg]
weight luggage & freight : 391 [kg]
operational weight loaded: 8376 [kg](88.2 [%])
fuel reserve : 680.8 [kg] enough for 2.16 [hours] flying
possible additional useful load : 443 [kg]
operational weight fully loaded : 9500 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 9500 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 6.15 [kg/kW]
power loading (operational without useful load) : 4.32 [kg/kW]
power loading (Take-off) 1 PUF: 9.23 [kg/kW]
total power : 1543.6 [kW] at 2250 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 4.1 [g] at 1000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 2.0 [g]
design flight time : 2.93 [hours]
design cycles : 7476 sorties, design hours : 21927 [hours]
operational wing loading : 592 [N/m^2]
wing stress (3 g) during operation : 149 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -2.00 ["]
max. angle of attack (stalling angle) : 11.51 ["]
angle of attack at max. speed : 0.10 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° :0.17 [ ]
lift coefficient at max. angle of attack : 1.15 [ ]
lift coefficient at max. speed : 0.18 [ ]
induced drag coefficient at max. speed : 0.0017 [ ]
drag coefficient at max. speed : 0.0373 [ ]
drag coefficient (zero lift) : 0.0355 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 9185 [kg]): 123 [km/u]
landing speed at sea-level: 144 [km/hr]
min. drag speed (max endurance) : 166 [km/hr] at 2600 [m](power :33 [%])
min. power speed (max range) : 166 [km/hr] at 2600 [m] (power:33 [%])
max. rate of climb speed : 158.3 [km/hr] at sea-level
cruising speed : 249 [km/hr] op 2600 [m] (power:68 [%])
design speed prop : 263 [km/hr]
maximum speed : 277 [km/hr] op 910 [m] (power:99 [%])
climbing speed at sea-level : 599 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 149.6 [km/u]
emergency/TO power : 780 [hp] at 2503 [rpm]
static prop wash : 118 [km/u]
starttijd : 17 [s]
take-off distance at sea-level : 386 [m]
lift/drag ratio : 11.33 [ ]
climb to 1000m with max payload : 2.84 [min]
climb to 2000m with max payload : 6.43 [min]
climb to 3000m with max payload : 10.85 [min]
practical ceiling (operational weight 6676 [kg] ) : 7568 [m]
practical ceiling fully loaded (mtow- 30 min.fuel:9342 [kg] ) : 5938 [m]
calculation *10* (action radius & endurance)
published range : 914 [km] with 3 crew and 2299.4 [kg] useful load and 88.1 [%] fuel
range : 1388 [km] with 3 crew and 1700.0 [kg] useful load and 133.8 [%] fuel
range : 1563 [km] with 17.0 passengers with each 10 [kg] luggage and 150.7 [%] fuel
Available Seat Kilometers (ASK) : 26575 [paskm]
max range theoretically with additional fuel tanks total 4933.7 [litre] fuel : 2862 [km]
useful load with range 500km : 2985 [kg]
useful load with range 500km : 17 passengers
production (useful load): 744.05 [tonkm/hour]
production (passengers): 4238.10 [paskm/hour]
combi aircraft mail/freight/passengers
oil and fuel consumption per tonkm : 0.46 [kg]
oil and fuel consumption per paskm : 0.05 [kg]
fuel cost per paskm : 0.05 [eur]
crew cost per paskm : 0.04 [eur]
economic hours : 12775 [hours] is less then design hours
time between engine failure : 40 [hr]
writing off per paskm : 0.05 [eur]
insurance per paskm : 0.03 [eur]
maintenance cost per paskm : 0.24 [eur]
direct operating cost per paskm : 0.41 [eur]
direct operating cost per tonkm : 4.10 [eur]
Literature :
Piston-engined airlines page 27,28
Praktisch handboek vliegtuigen deel 2 page 136,137
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 18 September 2021 contact : info.aircraftinvestigation@gmail.com python 3.7.4