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weight and performance calculations for the Tupolev PS-9
Tupolev PS-9
role : medium weight passenger aircraft
importance : ****
first flight : operational : June 1933
country : Russia
design : Andrei Tupolev , Sergei Ivanovich Komarov
production : ca. 70 aircraft
general information :
Conversion of the 3-engined ANT-9 in a two-engined version as proposed by Sergei
Ivanovich Komarov. Production started in 1933
users : Aeroflot, Turkish postal service
crew : 2 passengers : 9
engine : 2 Mikulin M-17 liquid-cooled 12 -cylinder V-engine 680 [hp](507.1 KW)
normal rating without supercharger
dimensions :
wingspan : 23.85 [m], length : 17.01 [m], height : 5.0 [m]
wing area : 84.0 [m^2]
weights :
max.take-off weight : 6200 [kg]
empty weight operational : 4400 [kg] useful load : 900 [kg]
performance :
maximum speed :237 [km/hr] at sea-level
cruise speed :225 [km/u] op 100 [m]
service ceiling : 5100 [m]
range : 700 [km]
description :
high-winged monoplane with fixed landing gear and tail strut
tapered wing with no flaps airfoil : Tupolev A0
engines and landing gear attached to the wings, fueltanks in the wings
construction : all-metal stressed-skin (duraluminium) airplane
airscrew :
two fixed pitch 2 -bladed tractor airscrews with max. efficiency :0.74 [ ]
estimated diameter airscrew 3.17 [m]
power loading prop : 159.96 [KW/m]
pitch angle prop : 18.29 [ ]
fixed angle prop : 23.29 [ ]
reduction : 1.00 [ ]
airscrew revs : 1600 [r.p.m.]
pitch at Max speed 2.41 [m]
blade-tip speed at max.continous speed : 273 [m/s]
propellor noise in flight : 95 [Db]
calculation : *1* (dimensions)
measured wing chord : 3.80 [m] at 50% wingspan
mean wing chord : 3.52 [m]
calculated average wing chord tapered wing with rounded tips: 3.53 [m]
wing aspect ratio : 6.8 []
corrected wing aspect ratio : 6.8 []
seize (span*length*height) : 2028 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 9.1 [kg/hr]
fuel consumption(cruise speed) : 199.7 [kg/hr] (272.5 [litre/hr]) at 63 [%] power
distance flown for 1 kg fuel : 1.13 [km/kg] at 2550 [m] height, sfc : 313.0 [kg/kwh]
estimated total fuel capacity : 962 [litre] (705 [kg])
calculation : *3* (weight)
weight engine(s) dry : 1080.0 [kg] = 1.06 [kg/KW]
weight 63.3 litre oil tank : 5.38 [kg]
oil tank filled with 7.6 litre oil : 6.8 [kg]
oil in engine 56.5 litre oil : 50.7 [kg]
fuel in engine 6.9 litre fuel : 5.07 [kg]
weight 115.9 litre gravity patrol tank(s) : 17.4 [kg]
weight radiator : 145.3 [kg]
weight exhaust pipes & fuel lines 60.9 [kg]
weight Burgess type silencers : 20.3 [kg]
weight starter (E.H.I. - Electric Hand Inertia): 12.4 [kg]
weight cowling 20.3 [kg]
weight airscrew(s) incl. boss & bolts : 96.8 [kg]
total weight propulsion system : 1521 [kg](24.5 [%])
***************************************************************
fuselage aluminium frame : 624 [kg]
cabin layout : pitch : 87 [cm] (1+1) seating in 4.5 rows
weight toilet : 8 [kg]
weight 2 fire extinguisher : 6 [kg]
weight 11 windows : 9.9 [kg]
weight door : 5.0 [kg]
passenger cabin max.width : 1.45 [m] cabin length : 5.08 [m] cabin height : 1.90 [m]
weight cabin furbishing : 27.5 [kg]
weight cabin floor : 41.5 [kg]
fuselage covering ( 69.0 [m2] duraluminium 2.23 [mm]) : 405.1 [kg]
fuselage (sound proof) isolation : 20.0 [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 : 2.2 [kg]
weight electricity generator : 2.2 [kg]
weight dual controls + indicators: 24.8 [kg]
weight seats : 55.0 [kg]
weight air conditioning : 14 [kg]
total weight fuselage : 1236 [kg](19.9 [%])
***************************************************************
total weight aluminium ribs (90 ribs) : 221 [kg]
weight engine mounts : 51 [kg]
weight two 423 [litre] main fuel tanks empty : 67.7 [kg]
weight wing covering (painted aluminium 0.82 [mm]) : 370 [kg]
total weight 4 aluminium spars : 288 [kg]
weight wings : 879 [kg]
weight wing/square meter : 10.47 [kg]
cantilever wing without bracing cables
weight fin & rudder (6.6 [m2]) : 70.1 [kg]
weight stabilizer & elevator (9.4 [m2]): 99.6 [kg]
total weight wing surfaces & bracing : 1167 [kg] (18.8 [%])
*******************************************************************
wheel pressure : 3100.0 [kg]
weight 2 Dunlop-type wheels (1130 [mm] by 205 [mm]) : 155.1 [kg]
weight tailskid : 15.1 [kg]
weight wheel-brakes : 5.3 [kg]
weight shock absorbers : 7.1 [kg]
weight undercarriage with axle 155.3 [kg]
total weight landing gear : 338.0 [kg] (5.5 [%]
*******************************************************************
********************************************************************
calculated empty weight : 4262 [kg](68.7 [%])
weight oil for 3.7 hours flying : 34.1 [kg]
weight cooling fluids : 219.1 [kg]
calculated operational weight empty : 4516 [kg] (72.8 [%])
published operational weight empty : 4400 [kg] (71.0 [%])
weight crew : 162 [kg]
weight fuel for 2.0 hours flying : 399 [kg]
********************************************************************
operational weight empty: 5077 [kg](81.9 [%])
weight 9 passengers : 693 [kg]
weight luggage & freight : 207 [kg]
operational weight loaded: 5977 [kg](96.4 [%])
fuel reserve : 223.0 [kg] enough for 1.12 [hours] flying
operational weight fully loaded : 6200 [kg] with fuel tank filled for 88 [%]
published maximum take-off weight : 6200 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (Take-off) : 6.11 [kg/kW]
PS-9 “Krokodil” used for propaganda.
power loading (operational without useful load) : 5.01 [kg/kW]
power loading (Take-off) 1 PUF: 12.23 [kg/kW]
total power : 1014.2 [kW] at 1600 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 3.0 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 2.1 [g]
design flight time : 2.49 [hours]
design cycles : 6956 sorties, design hours : 17301 [hours]
operational wing loading : 593 [N/m^2]
wing stress (3 g) during operation : 170 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.34 ["]
max. angle of attack (stalling angle) : 12.61 ["]
angle of attack at max. speed : 1.41 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.11 [ ]
lift coefficient at max. speed : 0.23 [ ]
lift coefficient at max. angle of attack : 1.14 [ ]
induced drag coefficient at max.speed : 0.0032 [ ]
drag coefficient at max. speed : 0.0546 [ ]
drag coefficient (zero lift) : 0.0514 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 6000 [kg]): 114 [km/u]
landing speed at sea-level (normal landing weight : 5161 [kg]): 121 [km/hr]
can not take-off with MTOW from airport 1000 [m] above sea level
max. rate of climb speed : 140 [km/hr] at sea-level
max. endurance speed : 121 [km/u] min.fuel/hr : 125 [kg/hr] at height : 610 [m]
max. range speed : 175 [km/u] min. fuel consumption : 0.851 [kg/km] at cruise height :
4267 [m]
cruising speed : 225 [km/hr] at 2550 [m] (power:79 [%])
max. continuous speed : 231.08 [km/hr]
maximum speed : 237 [km/hr] at 100 [m] (power:108 [%])
climbing speed at sea-level (loaded) : 379 [m/min]
climbing speed at 1000 [m] with 1 engine out (reduced useful load : 450 [kg]) : 38
[m/min]
calculation : *9* (regarding various performances)
take-off speed : 138.9 [km/u]
static prop wash : 140 [km/u]
take-off distance at sea-level gras field : 280 [m]
take-off distance at sea-level over 15 [m] height : 372 [m]
landing run : 179 [m]
lift/drag ratio : 8.80 [ ]
climb to 1000m with max payload : 3.55 [min]
climb to 2000m with max payload : 8.31 [min]
climb to 3000m with max payload : 15.36 [min]
practical ceiling (operational weight empty 5077 [kg] ) : 5800 [m]
practical ceiling fully loaded (mtow- 30 min.fuel:6100 [kg] ) : 4800 [m]
calculation *10* (action radius & endurance)
published range : 700 [km] with 2 crew and 901.5 [kg] useful load and 88.1 [%] fuel
range : 702 [km] with 2 crew and 900.0 [kg] useful load and 88.3 [%] fuel
range : 834 [km] with 9.0 passengers with each 10 [kg] luggage and 104.9 [%] fuel
Available Seat Kilometres (ASK) : 7502 [paskm]
max range theoretically with additional fuel tanks total 2187.6 [litre] fuel : 1884 [km]
useful load with range 500km : 1160 [kg]
useful load with range 500km : 9 passengers
production (useful load): 261 [tonkm/hour]
production (passengers): 2026 [paskm/hour]
oil and fuel consumption per tonkm : 0.80 [kg]
fuel cost per paskm : 0.080 [eur]
crew cost per paskm : 0.057 [eur]
economic hours : 12775 [hours] is less then design hours
time between engine failure : 595 [hr]
can continue fly on 1 engine, low risk for emergency landing for PUF
writing off per paskm : 0.106 [eur]
insurance per paskm : 0.010 [eur]
maintenance cost per paskm : 0.244 [eur]
direct operating cost per paskm : 0.497 [eur]
direct operating cost per tonkm : 4.972 [eur]
Literature :
Praktisch handboek vliegtuigen deel 2 page 277
Piston-engined airliners page 41
Tupolev ANT-9 | Bureau of Aircraft Accidents Archives (baaa-acro.com)
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
notes :