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weight and performance calculations for the Junkers Ju.160
Junkers Ju.160
role : light passenger aircraft
importance : ****
first flight : 30 January 1934 operational : January 1935
country : Germany
design :
production : 48 aircraft
general information :
Developed from the Ju.60. High speed airliner comparable and competing with the
Lockheed Orion and Heinkel 70. Used by the Luftwaffe mainly on its domestic lines up
until 1941.
users : Lufthansa (21)
registrations : D-UNOR, D-UVUX
crew : 2 passengers : 6
powerplant : 1 BMW 132E air-cooled 9 -cylinder radial engine 660 [hp](492.2 KW)
normal rating without supercharger
and with 700 [hp](522.0 KW) available for take-off
dimensions :
wingspan : 14.32 [m], length : 12.0 [m], height : 4.0 [m]
wing area : 34.8 [m^2]
weights :
max.take-off weight : 3550 [kg]
empty weight operational : 2320 [kg] useful load : 600 [kg]
performance :
maximum speed :340 [km/hr] at sea-level
cruise speed :323 [km/u] op 100 [m]
service ceiling : 5200 [m]
range : 1200 [km]
description :
low-winged monoplane with fixed landing gear with tail wheel
tapered wing with Junkers flaps airfoil : Junkers type
engine in the nose, fuel tanks in the wing, landing gear attached to the wing
construction : all-metal stressed-skin (duraluminium) airplane
airscrew :
Hamilton Standard variable pitch 2-bladed tractor airscrew with max. efficiency :
0.70 [ ]
estimated diameter airscrew 2.97 [m]
power loading prop : 165.71 [KW/m]
angle of attack prop at max. speed : 30.70 [ ]
reduction : 0.62 [ ]
airscrew revs : 1364 [r.p.m.]
pitch at Max speed 4.05 [m]
blade-tip speed at max.continous speed : 231 [m/s]
propellor noise in flight : 81 [Db]
calculation : *1* (dimensions)
measured wing chord : 2.23 [m] at 50% wingspan
mean wing chord : 2.43 [m]
calculated average wing chord tapered wing with rounded tips: 2.44 [m]
wing aspect ratio : 5.9 []
corrected wing aspect ratio : 5.9 []
seize (span*length*height) : 687 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 7.9 [kg/hr]
fuel consumption(cruise speed) : 92.2 [kg/hr] (125.8 [litre/hr]) at 62 [%] power
distance flown for 1 kg fuel : 3.50 [km/kg] at 2600 [m] height, sfc : 300.0 [kg/kwh]
estimated total fuel capacity : 530 [litre] (389 [kg])
calculation : *3* (weight)
weight engine(s) dry with reduction gear : 500.0 [kg] = 1.02 [kg/KW]
weight 51.4 litre oil tank : 4.37 [kg]
oil tank filled with 3.7 litre oil : 3.3 [kg]
oil in engine 2.7 litre oil : 2.5 [kg]
fuel in engine 3.4 litre fuel : 2.46 [kg]
weight 53.5 litre gravity patrol tank(s) : 8.0 [kg]
weight Burgess type silencers : 9.8 [kg]
weight starter (E.H.I. - Electric Hand Inertia): 12.1 [kg]
weight NACA cowling 22.0 [kg]
weight variable pitch control : 4.5 [kg]
weight airscrew(s) incl. boss & bolts : 40.7 [kg]
total weight propulsion system : 605 [kg](17.1 [%])
***************************************************************
fuselage aluminium frame : 325 [kg]
cabin layout : pitch : 87 [cm] (1+1) seating in 3.0 rows
weight 1 fire extinguisher : 3 [kg]
weight 8 windows : 7.2 [kg]
weight door : 5.0 [kg]
passenger cabin max.width : 1.27 [m] cabin length : 3.23 [m] cabin height : 1.80 [m]
weight cabin furbishing : 13.2 [kg]
weight cabin floor : 21.3 [kg]
fuselage covering ( 27.2 [m2] duraluminium 2.95 [mm]) : 206.0 [kg]
fuselage (sound proof) isolation : 4.8 [kg]
weight radio navigation equipment : 6.0 [kg]
weight Sperry gyro auto-pilot - course control equipment : 1.5 [kg]
weight instruments. : 5.0 [kg]
weight lighting : 1.5 [kg]
weight electricity generator : 1.5 [kg]
weight controls : 6.1 [kg]
weight seats : 40.0 [kg]
weight air conditioning : 5 [kg]
weight engine mounts & firewalls : 25 [kg]
total weight fuselage : 669 [kg](18.8 [%])
***************************************************************
total weight aluminium ribs (75 ribs) : 127 [kg]
weight fuel tanks empty for total 477 [litre] fuel : 38 [kg]
weight wing covering (painted aluminium 1.50 [mm]) : 283 [kg]
total weight aluminium spars (multi-cellular wing structure) : 209 [kg]
weight wings : 619 [kg]
weight wing/square meter : 17.78 [kg]
cantilever wing without bracing cables
weight rubber de-icing boots : 15.8 [kg]
weight fin & rudder (2.4 [m2]) : 42.7 [kg]
weight stabilizer & elevator (3.9 [m2]): 69.9 [kg]
weight fowler flap (2.9 [m2]) : 31.8 [kg]
total weight wing surfaces & bracing : 817 [kg] (23.0 [%])
*******************************************************************
Can only operate from paved runways
wheel pressure : 1775.0 [kg]
weight 2 Dunlop wheels (820 [mm] by 149 [mm]) : 102.7 [kg]
weight tailwheel(s) : 5.9 [kg]
weight Bendix wheel-brakes : 2.9 [kg]
weight Dowty shock absorbers : 3.9 [kg]
weight undercarriage with axle 99.5 [kg]
total weight landing gear : 214.8 [kg] (6.1 [%]
*******************************************************************
********************************************************************
calculated empty weight : 2306 [kg](65.0 [%])
weight oil for 4.5 hours flying : 35.1 [kg]
calculated operational weight empty : 2341 [kg] (65.9 [%])
published operational weight empty : 2320 [kg] (65.4 [%])
___o___
" "
weight crew : 162 [kg]
weight fuel for 2.0 hours flying : 184 [kg]
********************************************************************
operational weight empty: 2688 [kg](75.7 [%])
weight 6 passengers : 462 [kg]
weight luggage & freight : 138 [kg]
operational weight loaded: 3288 [kg](92.6 [%])
fuel reserve : 204.4 [kg] enough for 2.22 [hours] flying
possible additional useful load : 58 [kg]
operational weight fully loaded : 3550 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 3550 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 7.21 [kg/kW]
power loading (operational without useful load) : 5.46 [kg/kW]
total power : 492.2 [kW] at 2200 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 4.6 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 2.7 [g]
design flight time : 2.97 [hours]
design cycles : 11572 sorties, design hours : 34394 [hours]
operational wing loading : 757 [N/m^2]
wing stress (3 g) during operation : 128 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -2.17 ["]
max. angle of attack (stalling angle) : 12.20 ["]
angle of attack at max. speed : -0.38 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.17 [ ]
lift coefficient at max. speed : 0.14 [ ]
lift coefficient at max. angle of attack : 1.13 [ ]
max.lift coefficient full flaps : 1.38 [ ]
induced drag coefficient at max.speed : 0.0014 [ ]
drag coefficient at max. speed : 0.0204 [ ]
drag coefficient (zero lift) : 0.0190 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 3458 [kg]): 135 [km/u]
stalling speed at sea-level with full flaps (normal landing weight): 110 [km/u]
landing speed at sea-level (normal landing weight : 2810 [kg]): 127 [km/hr]
max. rate of climb speed : 149 [km/hr] at sea-level
max. endurance speed : 157 [km/u] min.fuel/hr : 55 [kg/hr] at height : 610 [m]
max. range speed : 249 [km/u] min. fuel consumption : 0.301 [kg/km] at cruise height :
4267 [m]
cruising speed : 323 [km/hr] at 2600 [m] (power:82 [%])
max. continuous speed : 331.50 [km/hr]
maximum speed : 340 [km/hr] at 100 [m] (power:111 [%])
climbing speed at sea-level (loaded) : 426 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 164.5 [km/u]
emergency/TO power : 700 [hp] at 2266 [rpm]
static prop wash : 113 [km/u]
high wheel pressure, can only take off from paved runways
take-off distance at sea-level concrete runway : 451 [m]
take-off distance at sea-level over 15 [m] height : 538 [m]
landing run : 200 [m]
lift/drag ratio : 13.49 [ ]
climb to 1000m with max payload : 3.50 [min]
climb to 2000m with max payload : 8.34 [min]
climb to 3000m with max payload : 15.96 [min]
practical ceiling (operational weight 2688 [kg] ) : 6100 [m]
practical ceiling fully loaded (mtow- 30 min.fuel:3504 [kg] ) : 4500 [m]
calculation *10* (action radius & endurance)
published range : 1200 [km] with 2 crew and 704.3 [kg] useful load and 88.1 [%] fuel
range : 1565 [km] with 2 crew and 600.0 [kg] useful load and 114.9 [%] fuel
range : 1839 [km] with 6.0 passengers with each 10 [kg] luggage and 135.0 [%] fuel
Available Seat Kilometres (ASK) : 11031 [paskm]
max range theoretically with additional fuel tanks total 1538.6 [litre] fuel : 3752 [km]
useful load with range 500km : 985 [kg]
useful load with range 500km : 6 passengers
production (useful load): 318 [tonkm/hour]
production (passengers): 1938 [paskm/hour]
oil and fuel consumption per tonkm : 0.31 [kg]
fuel cost per paskm : 0.031 [eur]
crew cost per paskm : 0.047 [eur]
economic hours : 12775 [hours] is less then design hours
time between engine failure : 2105 [hr]
in case of engine failure only option is emergency landing
writing off per paskm : 0.047 [eur]
insurance per paskm : 0.004 [eur]
maintenance cost per paskm : 0.085 [eur]
direct operating cost per paskm : 0.215 [eur]
direct operating cost per tonkm : 2.153 [eur]
Literature :
Praktisch handboek vliegtuigen deel 5 page 234,235
Piston-engined airliners page 40
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/
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(c) B van der Zalm 28 November 2021 contact : info.aircraftinvestigation@gmail.com python 3.7.4