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weight and performance calculations for the Tupolev ANT-14
Tupolev ANT-14 Pravda
role : commuter airliner / propaganda
importance : **
first flight : 14 August 1931 operational : March 1933
country : Russia
design : A.N. Tupolev
production : 1 prototype
general information :
Although there were no problems with the aircraft, the Aeroflot had no need for such a
big aircraft, and therefore it did not go into production. The sole aircraft built then was
used as flagship from March 1933 of the aerial propaganda squadron and was given
the name “Pravda” (Truth). Mostly it flew sightseeing flights over Moscow, but now
and then it made tourist flights to Kharkow and Leningrad. It carried 40.000
passengers until it was grounded in 1941, so it made at least 1100 flights !
The Gnome Rhone Jupiter engine was indicated as M-22 in the USSR.
users : CCCP propaganda squadron
crew : 3 passengers : 36
powerplant : 5 Gnome Rhone 9Akx Jupiter VI air-cooled 9 -cylinder radial engine 480
[hp] (357.9 KW)
normal rating without supercharger
dimensions :
wingspan : 40.4 [m], length : 26.49 [m], height : 5.4 [m]
wing area : 240.0 [m^2]
weights :
max.take-off weight : 17530 [kg]
empty weight operational : 10828 [kg] useful load : 3600 [kg]
performance :
maximum speed :236 [km/hr] at sea-level
cruise speed :224 [km/u] op 100 [m]
service ceiling : 4220 [m]
range : 900 [km]
description :
high-winged monoplane with fixed landing gear and tail strut
tapered wing with no flaps airfoil : Tupolev A0
4 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 stressed-skin (duraluminium) airplane
airscrew :
five fixed pitch 2 -bladed tractor airscrews with max. efficiency :0.69 [ ]
estimated diameter airscrew 3.67 [m]
relative pitch (J) : 0.70 [ ]
power loading prop : 97.53 [KW/m]
theoretical pitch without slip : 3.06 [m]
blade angle prop (fixed) : 19.47 [ ]
tip-speed close to speed of sound (above Mach 0.85) > loose of efficiency
reduction : 0.75 [ ]
airscrew revs : 1500 [r.p.m.]
pitch at Max speed 2.56 [m]
blade-tip speed at max.continous speed : 295 [m/s]
propellor noise in flight : 102 [Db]
calculation : *1* (dimensions)
measured wing chord : 5.78 [m] at 50% wingspan
mean wing chord : 5.94 [m]
calculated average wing chord tapered wing with rounded tips: 5.95 [m]
wing aspect ratio : 6.8 []
seize (span*length*height) : 5779 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 44.7 [kg/hr]
fuel consumption(cruise speed) : 401.7 [kg/hr] (548.0 [litre/hr]) at 68 [%] power
distance flown for 1 kg fuel : 0.56 [km/kg] at 2110 [m] height, sfc : 330.6 [kg/kwh]
estimated total fuel capacity : 2497 [litre] (1830 [kg])
calculation : *3* (weight)
weight engine(s) dry with reduction gear : 1975.0 [kg] = 1.10 [kg/KW]
weight 284.8 litre oil tank : 24.21 [kg]
oil tank filled with 13.4 litre oil : 12.0 [kg]
oil in engine 10.0 litre oil : 8.9 [kg]
fuel in engine 12.2 litre fuel : 8.95 [kg]
weight 233.0 litre gravity patrol tank(s) : 34.9 [kg]
weight Burgess type silencers : 35.8 [kg]
weight starter (E.H.I. - Electric Hand Inertia): 8.8 [kg]
weight cowling (Townend ring) 14.3 [kg]
weight airscrew(s) incl. boss & bolts : 305.4 [kg]
total weight propulsion system : 2428 [kg](13.9 [%])
***************************************************************
fuselage aluminium frame : 2082 [kg]
cabin layout : pitch : 87 [cm] (2+2) seating in 9.0 rows
weight two toilets : 16 [kg]
weight 4 fire extinguisher : 12 [kg]
weight pantry : 23.1 [kg]
weight garderobe : 18.0 [kg]
weight 20 windows : 18.0 [kg]
weight door : 5.0 [kg]
passenger cabin max.width : 2.56 [m] cabin length : 10.60 [m] cabin height : 1.90 [m]
weight cabin furbishing : 149.5 [kg]
weight cabin floor : 163.8 [kg]
fuselage covering ( 132.5 [m2] duraluminium 1.43 [mm]) : 500.6 [kg]
fuselage (sound proof) isolation : 48.1 [kg]
weight radio transceiver equipment : 7.0 [kg]
weight instruments. : 9.0 [kg]
weight lighting : 9.0 [kg]
weight electricity generator : 9.0 [kg]
weight controls : 13.2 [kg]
weight seats : 195.0 [kg]
weight air conditioning : 54 [kg]
weight engine mount and firewall : 18 [kg]
total weight fuselage : 3298 [kg](18.8 [%])
***************************************************************
total weight aluminium ribs (151 ribs) : 625 [kg]
weight engine mounts : 72 [kg]
weight fuel tanks empty for total 2264 [litre] fuel : 181 [kg]
weight wing covering (painted aluminium 1.16 [mm]) : 1502 [kg]
total weight 4 aluminium spars : 1166 [kg]
weight wings : 3293 [kg]
weight wing/square meter : 13.72 [kg]
cantilever wing without bracing cables
weight fin & rudder (18.9 [m2]) : 262.8 [kg]
weight stabilizer & elevator (27.0 [m2]): 372.3 [kg]
total weight wing surfaces & bracing : 4181 [kg] (23.9 [%])
*******************************************************************
wheel pressure : 4382.5 [kg]
weight 4 Dunlop-type wheels (1180 [mm] by 236 [mm]) : 377.1 [kg]
weight tail wheel : 32.4 [kg]
weight wheel-brakes : 14.4 [kg]
weight shock absorbers : 19.2 [kg]
weight undercarriage with axle 362.3 [kg]
total weight landing gear : 805.6 [kg] (4.6 [%]
*******************************************************************
********************************************************************
calculated empty weight : 10713 [kg](61.1 [%])
weight oil for 4.8 hours flying : 215.5 [kg]
calculated operational weight empty : 10929 [kg] (62.3 [%])
published operational weight empty : 10828 [kg] (61.8 [%])
***o***
"
weight crew : 243 [kg]
weight fuel for 2.0 hours flying : 803 [kg]
weight catering : 57.8 [kg]
weight water : 23.1 [kg]
********************************************************************
operational weight empty: 12056 [kg](68.8 [%])
weight 36 passengers : 2772 [kg]
weight luggage & freight : 828 [kg]
operational weight loaded: 15656 [kg](89.3 [%])
fuel reserve : 1026.9 [kg] enough for 2.56 [hours] flying
possible additional useful load : 847 [kg]
operational weight fully loaded : 17530 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 17530 [kg] (100.0 [%])
calculation : * 4 * (engine power)
power loading (Take-off) : 9.80 [kg/kW]
power loading (operational without useful load) : 6.74 [kg/kW]
power loading (Take-off) 1 PUF: 12.24 [kg/kW]
total power : 1789.7 [kW] at 2000 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 3.5 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 1.6 [g]
design flight time : 3.21 [hours]
design cycles : 3507 sorties, design hours : 11261 [hours]
operational wing loading : 493 [N/m^2]
wing stress (3 g) during operation : 108 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.34 ["]
max. angle of attack (stalling angle) : 12.60 ["]
angle of attack at max. speed : 0.96 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.11 [ ]
lift coefficient at max. speed : 0.19 [ ]
lift coefficient at max. angle of attack : 1.14 [ ]
induced drag coefficient at max.speed : 0.0022 [ ]
drag coefficient at max. speed : 0.0319 [ ]
drag coefficient (zero lift) : 0.0296 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 17128 [kg]): 114 [km/u]
landing speed at sea-level (normal landing weight : 12525 [kg]): 112 [km/hr]
max. rate of climb speed : 144 [km/hr] at sea-level
max. endurance speed : 136 [km/u] min.fuel/hr : 311 [kg/hr] at height : 610 [m]
max. range speed : 188 [km/u] min. fuel consumption : 1.951 [kg/km] at cruise height :
3353 [m]
cruising speed : 224 [km/hr] at 2110 [m] (power:88 [%])
max. continuous speed : 230.10 [km/hr]
maximum speed : 236 [km/hr] at 100 [m] (power:113 [%])
climbing speed at sea-level (loaded) : 209 [m/min]
climbing speed at 1000 [m] with 1 engine out (PUF / MTOW) : 52 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 138.1 [km/u]
static prop wash : 156 [km/u]
take-off distance at sea-level gras field : 242 [m]
take-off distance at sea-level over 15 [m] height : 415 [m]
landing run : 156 [m]
lift/drag ratio : 11.62 [ ]
climb to 1000m with max payload : 8.52 [min]
climb to 2000m with max payload : 22.19 [min]
climb to 3000m with max payload : 54.93 [min]
practical ceiling (operational weight empty 12056 [kg] ) : 5400 [m]
practical ceiling fully loaded (mtow- 30 min.fuel:17329 [kg] ) : 3100 [m]
calculation *10* (action radius & endurance)
published range : 900 [km] with 3 crew and 4745.8 [kg] useful load and 88.1 [%] fuel
range : 1540 [km] with 3 crew and 3600.0 [kg] useful load and 150.7 [%] fuel
range : 1801 [km] with 36.0 passengers with each 10 [kg] luggage and 176.3 [%] fuel
Available Seat Kilometres (ASK) : 64826 [paskm]
max range theoretically with additional fuel tanks total 8895.5 [litre] fuel : 3343 [km]
useful load with range 500km : 5625 [kg]
useful load with range 500km : 36 passengers
production (useful load): 1261 [tonkm/hour]
production (passengers): 8071 [paskm/hour]
oil and fuel consumption per tonkm : 0.35 [kg]
fuel cost per paskm : 0.035 [eur]
crew cost per paskm : 0.024 [eur]
time between engine failure : 169 [hr]
writing off per paskm : 0.063 [eur]
insurance per paskm : 0.055 [eur]
maintenance cost per paskm : 0.147 [eur]
direct operating cost per paskm : 0.324 [eur]
direct operating cost per tonkm : 3.240 [eur]
Literature :
Praktisch handbook vliegtuigen deel 2 page 274,275
Piston-engined airliners page 41
Wikipedia
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 28 November 2021 contact : info.aircraftinvestigation@gmail.com python 3.7.4