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weight and performance calculations for the Tupolev ANT-35
Tupolev ANT-35bis
role : medium weight passenger aircraft
importance : **
first flight : 20 August 1936 flown by Mikhail Gromov operational : July 1937
country : Russia
design : Aleksander Arkhangelski
production : 11 aircraft
general information :
Prototype was fitted with Gnome Rhone 14K engines (license built in USSR by
Tumansky , and designated M-85). But soon more powerful 1000 hp Wright Cyclones
were installed, license built as Shetsov M-62IR . Also the headroom was increased from
1.63m to 1.85m cabin height. This version was indicated as ANT-35bis. Performance
was good and production started. But in 1939 license built Douglas DC-3’s came into
service with Aeroflot. The DC-3 could carry twice as many passengers over a greater
range, resulting in production stop of the ANT-35
users : Aeroflot
crew : 2 passengers : 10
powerplant : 2 Shetsov Ash-62IR (M-62IR) air-cooled 9 -cylinder radial engine 850
[hp](633.8 KW) normal rating, supercharged engine, high blower, constant power to
height : 4200 [m] and with 1000 [hp](745.7 KW) available for take-off
dimensions :
wingspan : 20.8 [m], length : 15.4 [m], height : 5.66 [m]
wing area : 57.8 [m^2]
weights :
max.take-off weight : 7000 [kg]
empty weight operational : 5010 [kg] useful load : 1000 [kg]
performance :
maximum speed :392 [km/u] op 2000 [m]
cruise speed :372 [km/u] op 2000 [m]
service ceiling : 7200 [m]
range : 800 [km]
description :
low-winged monoplane with retractable landing gear with tail wheel
tapered wing with split flap airfoil : unknown
engines and landing gear attached to the wings, fuel tanks in the wings
construction : all-metal stressed-skin (duraluminium) airplane
airscrew :
two Hamilton Standard constant speed 3 -bladed tractor airscrews with max. efficiency
:0.74 [ ]
estimated diameter airscrew 3.30 [m]
relative pitch (J) : 1.47 [ ]
power loading prop : 128.05 [KW/m]
theoretical pitch without slip : 5.43 [m]
blade angle prop at max.speed : 35.95 [ ]
Measured chord at root : 3.96m at 50% span : 2.80m
reduction : 0.62 [ ]
airscrew revs : 1312 [r.p.m.]
aerodynamic pitch at max. continuous speed 4.85 [m]
blade-tip speed at max. continuous speed : 250 [m/s]
propellor noise in flight : 87 [Db]
calculation : *1* (dimensions)
measured wing chord : 2.80 [m] at 50% wingspan
mean wing chord : 2.78 [m]
calculated average wing chord tapered wing with rounded tips: 2.71 [m]
wing aspect ratio : 7.5 []
seize (span*length*height) : 1813 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 17.7 [kg/hr]
fuel consumption(cruise speed) : 427.8 [kg/hr] (583.7 [litre/hr]) at 90 [%] power
distance flown for 1 kg fuel : 0.87 [km/kg] at 3600 [m] height, sfc : 375.0 [kg/kwh]
estimated total fuel capacity : 1425 [litre] (1044 [kg])
calculation : *3* (weight)
weight engine(s) dry with reduction gear : 1120.0 [kg] = 0.88 [kg/KW]
weight 82.7 litre oil tank : 7.03 [kg]
oil tank filled with 9.5 litre oil : 8.5 [kg]
oil in engine 7.1 litre oil : 6.3 [kg]
fuel in engine 8.6 litre fuel : 6.34 [kg]
weight 248.2 litre gravity patrol tank(s) : 37.2 [kg]
weight Burgess type silencers : 25.4 [kg]
weight starter : 15.5 [kg]
weight NACA cowling 28.4 [kg]
weight variable pitch control : 13.8 [kg]
weight airscrew(s) incl. boss & bolts : 179.6 [kg]
total weight propulsion system : 1434 [kg](20.5 [%])
***************************************************************
fuselage aluminium frame : 762 [kg]
cabin layout : pitch : 87 [cm] (1+1) seating in 5.0 rows
weight toilet : 8 [kg]
weight 2 fire extinguisher : 6 [kg]
weight 12 windows : 10.8 [kg]
weight door : 5.0 [kg]
passenger cabin max.width : 1.47 [m] cabin length : 5.52 [m] cabin height : 1.83 [m]
weight cabin furbishing : 29.4 [kg]
weight cabin floor : 46.0 [kg]
fuselage covering ( 61.0 [m2] duraluminium 3.08 [mm]) : 491.2 [kg]
fuselage (sound proof) isolation : 13.7 [kg]
weight radio transceiver equipment : 7.0 [kg]
weight Sperry gyro auto-pilot - course control equipment : 1.5 [kg]
weight instruments. : 6.0 [kg]
weight lighting : 2.5 [kg]
weight electricity generator : 6.0 [kg]
weight dual controls + indicators: 23.0 [kg]
weight seats : 60.0 [kg]
weight air conditioning : 15 [kg]
total weight fuselage : 1472 [kg](21.0 [%])
***************************************************************
total weight aluminium ribs (129 ribs) : 250 [kg]
weight engine mounts : 63 [kg]
weight two 588 [litre] main fuel tanks empty : 94.1 [kg]
weight wing covering (painted aluminium 1.66 [mm]) : 518 [kg]
total weight aluminium spars (multi-cellular wing structure) : 356 [kg]
weight wings : 1124 [kg]
weight wing/square meter : 19.44 [kg]
cantilever wing without bracing cables
weight rubber de-icing boots : 22.9 [kg]
weight fin & rudder (5.0 [m2]) : 98.4 [kg]
weight stabilizer & elevator (6.5 [m2]): 126.9 [kg]
weight split flap (2.9 [m2]) : 31.1 [kg]
total weight wing surfaces & bracing : 1561 [kg] (22.3 [%])
*******************************************************************
Can only operate from paved runways
wheel pressure : 3500.0 [kg]
weight 2 Dunlop-type wheels (990 [mm] by 198 [mm]) : 174.7 [kg]
weight tailwheel(s) : 5.9 [kg]
weight wheel-brakes : 6.0 [kg]
weight shock absorbers : 8.0 [kg]
weight wheel hydraulic operated retraction system : 33.5 [kg]
weight undercarriage with axle 274.0 [kg]
total weight landing gear : 502.1 [kg] (7.2 [%]
*******************************************************************
********************************************************************
calculated empty weight : 4969 [kg](71.0 [%])
weight oil for 2.6 hours flying : 45.8 [kg]
calculated operational weight empty : 5014 [kg] (71.6 [%])
published operational weight empty : 5010 [kg] (71.6 [%])
weight crew : 162 [kg]
weight fuel for 1.5 hours flying : 642 [kg]
weight catering : 8.6 [kg]
weight water : 3.4 [kg]
********************************************************************
operational weight empty: 5830 [kg](83.3 [%])
weight 10 passengers : 770 [kg]
weight luggage & freight : 230 [kg]
operational weight loaded: 6830 [kg](97.6 [%])
fuel reserve : 169.7 [kg] enough for 0.40 [hours] flying
operational weight fully loaded : 7000 [kg] with fuel tank filled for 78 [%]
published maximum take-off weight : 7000 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 5.52 [kg/kW]
power loading (operational without useful load) : 4.60 [kg/kW]
power loading (Take-off) 1 PUF: 11.04 [kg/kW]
total power : 1267.7 [kW] at 2100 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 4.9 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 2.5 [g]
design flight time : 1.72 [hours]
design cycles : 14257 sorties, design hours : 24528 [hours]
operational wing loading : 989 [N/m^2]
wing stress (3 g) during operation : 153 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.30 ["]
max. angle of attack (stalling angle) : 12.24 ["]
angle of attack at max. speed : 0.66 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.11 [ ]
lift coefficient at max. speed : 0.17 [ ]
lift coefficient at max. angle of attack : 1.15 [ ]
max.lift coefficient full flaps : 1.25 [ ]
induced drag coefficient at max.speed : 0.0015 [ ]
drag coefficient at max. speed : 0.0268 [ ]
drag coefficient (zero lift) : 0.0253 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 6572 [kg]): 143 [km/u]
stalling speed at sea-level with full flaps (normal landing weight): 130 [km/u]
landing speed at sea-level (normal landing weight : 5918 [kg]): 150 [km/hr]
max. rate of climb speed : 147 [km/hr] at sea-level
max. endurance speed : 151 [km/u] min.fuel/hr : 115 [kg/hr] at height : 610 [m]
max. range speed : 231 [km/u] at cruise height : 4267 [m]
cruising speed : 372 [km/hr] at 3600 [m] (power:83 [%])
max. continuous speed : 381.79 [km/hr]
maximum speed : 392 [km/hr] at 2000 [m] (power:109 [%])
climbing speed at sea-level (loaded) : 630 [m/min]
climbing speed at 1000 [m] with 1 engine out (PUF / MTOW) : 260 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 177.5 [km/u]
emergency/TO power : 1000 [hp] at 2278 [rpm]
static prop wash : 156 [km/u]
high wheel pressure, can only take off from paved runways
take-off distance at sea-level concrete runway : 282 [m]
take-off distance at sea-level over 15 [m] height : 341 [m]
landing run : 284 [m]
lift/drag ratio : 13.38 [ ]
climb to 1000m with max payload : 1.68 [min]
climb to 2000m with max payload : 3.38 [min]
climb to 3000m with max payload : 5.11 [min]
practical ceiling (operational weight empty 5830 [kg] ) : 9800 [m]
practical ceiling fully loaded (mtow- 30 min.fuel:6786 [kg] ) : 9100 [m]
calculation *10* (action radius & endurance)
published range : 800 [km] with 2 crew and 903.4 [kg] useful load and 88.1 [%] fuel
range : 716 [km] with 2 crew and 1000.0 [kg] useful load and 78.9 [%] fuel
range : 829 [km] with 10.0 passengers with each 10 [kg] luggage and 91.3 [%] fuel
Available Seat Kilometres (ASK) : 8291 [paskm]
max range theoretically with additional fuel tanks total 2598.2 [litre] fuel : 2802 [km]
useful load with range 500km : 1329 [kg]
useful load with range 500km : 10 passengers
production (useful load): 495 [tonkm/hour]
production (passengers): 3720 [paskm/hour]
oil and fuel consumption per tonkm : 0.90 [kg]
fuel cost per paskm : 0.090 [eur]
crew cost per paskm : 0.030 [eur]
economic hours : 12775 [hours] is less then design hours
time between engine failure : 1010 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
writing off per paskm : 0.065 [eur]
insurance per paskm : 0.005 [eur]
maintenance cost per paskm : 0.151 [eur]
direct operating cost per paskm : 0.342 [eur]
direct operating cost per tonkm : 3.423 [eur]
Literature :
Piston-engined airliners page 41
Praktisch handboek vliegtuigen deel 5 page
Wikipedia
Tupolev: The Man and His Aircraft - Paul Duffy, A. I. Kandalov - Google Boeken
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 22 January 2022 contact : info.aircraftinvestigation@gmail.com python 3.7.4