Aircraft investigation >>>>>>> HOME PAGE
weight and performance calculations for the Tupolev ANT-9
Early ANT-9 with Gnome Rhone Titan engines
Tupolev ANT-9
role : medium weight passenger aircraft
importance : ****
first flight : 5 May 1929 operational : August 1929
country : USSR
design : Andrei Tupolev
production : 30 aircraft
general information :
Prototype and early production had Gnome-Rhone Titan 5K 240 hp engines.
Later they were replaced by imported Wright Whirlwind J-6 305-320 hp
Engines giving better performance for speed and ceiling.
The Deruluft used the ANT-9 on its Moscow – Berlin route. Design bears resemblance
with the American 4-AT “Tin Goose”
Users : Deruluft, Aeroflot
crew : 2 passengers : 9
powerplant : 3 Gnome Rhone Titan 5K air-cooled 5 -cylinder radial engine 240
[hp](179.0 KW) normal rating without supercharger and with 285 [hp] (212.5 KW)
available for take-off
dimensions :
wingspan : 23.7 [m], length : 16.8 [m], height : 5.0 [m]
wing area : 84.0 [m^2]
weights :
max.take-off weight : 5200 [kg]
empty weight operational : 3353 [kg] useful load : 900 [kg]
performance :
maximum speed :184 [km/u] op 100 [m]
cruise speed :175 [km/u] op 100 [m]
service ceiling : 3750 [m]
range : 1000 [km]
description :
high-winged monoplane with fixed landing gear and tail strut
tapered wing with no flaps airfoil : Tupolev
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 :
three fixed pitch 2 -bladed tractor airscrews with max. efficiency :0.68 [ ]
estimated diameter airscrew 2.93 [m]
ANT-9 with Gnome Rhone Titan engines, measured chord at root : 4.53 [m]
power loading prop : 61.08 [KW/m]
pitch angle prop : 13.88 [ ]
fixed angle prop : 18.88 [ ]
fine pitch
reduction : 1.00 [ ]
airscrew revs : 1800 [r.p.m.]
pitch at Max speed 1.66 [m]
blade-tip speed at max.continous speed : 281 [m/s]
propellor noise in flight : 97 [Db]
calculation : *1* (dimensions)
measured wing chord : 4.03 [m] at 50% wingspan
mean wing chord : 3.54 [m]
calculated average wing chord tapered wing with rounded tips: 3.55 [m]
wing aspect ratio : 6.7 []
corrected wing aspect ratio : 6.7 []
seize (span*length*height) : 1991 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 13.4 [kg/hr]
fuel consumption(cruise speed) : 117.2 [kg/hr] (159.8 [litre/hr]) at 70 [%] power
distance flown for 1 kg fuel : 1.49 [km/kg] at 1875 [m] height, sfc : 310.9 [kg/kwh]
estimated total fuel capacity : 1037 [litre] (760 [kg])
calculation : *3* (weight)
weight engine(s) dry : 720.0 [kg] = 1.34 [kg/KW]
weight 115.9 litre oil tank : 9.86 [kg]
oil tank filled with 4.0 litre oil : 3.6 [kg]
oil in engine 3.0 litre oil : 2.7 [kg]
fuel in engine 3.7 litre fuel : 2.68 [kg]
weight 68.0 litre gravity patrol tank(s) : 10.2 [kg]
weight starter (E.H.I. - Electric Hand Inertia): 4.4 [kg]
weight airscrew(s) incl. boss & bolts : 72.2 [kg]
total weight propulsion system : 826 [kg](15.9 [%])
***************************************************************
fuselage aluminium frame : 566 [kg]
cabin layout : pitch : 87 [cm] (1+1) seating in 4.5 rows
weight toilet : 8 [kg]
weight 2 fire extinguisher : 6 [kg]
weight 9 windows : 8.1 [kg]
weight door : 5.0 [kg]
passenger cabin max.width : 1.34 [m] cabin length : 5.08 [m] cabin height : 1.90 [m]
weight cabin furbishing : 24.9 [kg]
weight cabin floor : 38.3 [kg]
fuselage covering ( 53.3 [m2] duraluminium 2.62 [mm]) : 366.6 [kg]
weight radio transceiver equipment : 7.0 [kg]
weight instruments. : 7.0 [kg]
weight lighting : 2.2 [kg]
weight electricity generator : 2.2 [kg]
weight dual controls + indicators: 25.6 [kg]
weight seats : 55.0 [kg]
weight air conditioning : 8 [kg]
weight engine mount and firewall : 9 [kg]
total weight fuselage : 1137 [kg](21.9 [%])
***************************************************************
total weight aluminium ribs (75 ribs) : 185 [kg]
weight engine mounts : 18 [kg]
weight fuel tanks empty for total 969 [litre] fuel : 77 [kg]
weight wing covering (painted aluminium 0.74 [mm]) : 334 [kg]
total weight 4 aluminium spars : 285 [kg]
weight wings : 804 [kg]
weight wing/square meter : 9.58 [kg]
cantilever wing without bracing cables
weight fin & rudder (6.5 [m2]) : 63.4 [kg]
weight stabilizer & elevator (9.4 [m2]): 91.1 [kg]
total weight wing surfaces & bracing : 1054 [kg] (20.3 [%])
*******************************************************************
wheel pressure : 2600.0 [kg]
weight 2 wheels (1150 [mm] by 177 [mm]) : 142.1 [kg]
weight tailskid : 13.9 [kg]
weight bungee cord shock absorbers : 5.7 [kg]
weight undercarriage with axle 145.7 [kg]
total weight landing gear : 307.4 [kg] (5.9 [%]
*******************************************************************
********************************************************************
calculated empty weight : 3324 [kg](63.9 [%])
weight oil for 6.9 hours flying : 92.0 [kg]
calculated operational weight empty : 3416 [kg] (65.7 [%])
published operational weight empty : 3353 [kg] (64.5 [%])
***o***
"
weight crew : 162 [kg]
weight fuel for 2.0 hours flying : 234 [kg]
********************************************************************
operational weight empty: 3812 [kg](73.3 [%])
weight 9 passengers : 693 [kg]
weight luggage & freight : 207 [kg]
operational weight loaded: 4712 [kg](90.6 [%])
fuel reserve : 487.6 [kg] enough for 4.16 [hours] flying
operational weight fully loaded : 5200 [kg] with fuel tank filled for 95 [%]
published maximum take-off weight : 5200 [kg] (100.0 [%])
||
I||
I=||==|
I||
||
calculation : * 4 * (engine power)
power loading (Take-off) : 9.69 [kg/kW]
power loading (operational without useful load) : 7.10 [kg/kW]
power loading (Take-off) 1 PUF: 14.53 [kg/kW]
total power : 536.9 [kW] at 1800 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 2.4 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 2.3 [g]
design flight time : 4.00 [hours]
design cycles : 5288 sorties, design hours : 21154 [hours]
operational wing loading : 445 [N/m^2]
wing stress (3 g) during operation : 139 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.35 ["]
max. angle of attack (stalling angle) : 12.65 ["]
angle of attack at max. speed : 2.09 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.11 [ ]
lift coefficient at max. speed : 0.28 [ ]
lift coefficient at max. angle of attack : 1.14 [ ]
induced drag coefficient at max.speed : 0.0050 [ ]
drag coefficient at max. speed : 0.0562 [ ]
drag coefficient (zero lift) : 0.0512 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 5083 [kg]): 105 [km/u]
landing speed at sea-level (normal landing weight : 3979 [kg]): 107 [km/hr]
max. rate of climb speed : 114 [km/hr] at sea-level
max. endurance speed : 112 [km/u] min.fuel/hr : 95 [kg/hr] at height : 610 [m]
max. range speed : 148 [km/u] min. fuel consumption : 0.752 [kg/km] at cruise height :
3048 [m]
cruising speed : 175 [km/hr] at 1875 [m] (power:90 [%])
max. continuous speed : 179.61 [km/hr]
maximum speed : 184 [km/hr] at 100 [m] (power:113 [%])
climbing speed at sea-level (loaded) : 192 [m/min]
climbing speed at 1000 [m] with 1 engine out (PUF / MTOW) : 37 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 127.2 [km/u]
emergency/TO power : 285 [hp] at 1962 [rpm]
static prop wash : 160 [km/u]
take-off distance at sea-level gras field : 143 [m]
take-off distance at sea-level over 15 [m] height : 291 [m]
landing run : 138 [m]
lift/drag ratio : 8.76 [ ]
climb to 1000m with max payload : 9.47 [min]
climb to 2000m with max payload : 25.98 [min]
practical ceiling (operational weight empty 3812 [kg] ) : 4800 [m]
practical ceiling fully loaded (mtow- 30 min.fuel:5141 [kg] ) : 2800 [m]
calculation *10* (action radius & endurance)
published range : 1000 [km] with 2 crew and 952.4 [kg] useful load and 88.1 [%] fuel
range : 1078 [km] with 2 crew and 900.0 [kg] useful load and 95.0 [%] fuel
range : 1253 [km] with 9.0 passengers with each 10 [kg] luggage and 110.4 [%] fuel
Available Seat Kilometres (ASK) : 11278 [paskm]
max range theoretically with additional fuel tanks total 2323.3 [litre] fuel : 2265 [km]
useful load with range 500km : 1368 [kg]
useful load with range 500km : 9 passengers
production (useful load): 239 [tonkm/hour]
production (passengers): 1575 [paskm/hour]
oil and fuel consumption per tonkm : 0.55 [kg]
fuel cost per paskm : 0.055 [eur]
crew cost per paskm : 0.063 [eur]
economic hours : 12775 [hours] is less then design hours
time between engine failure : 600 [hr]
writing off per paskm : 0.090 [eur]
insurance per paskm : 0.003 [eur]
maintenance cost per paskm : 0.207 [eur]
direct operating cost per paskm : 0.418 [eur]
direct operating cost per tonkm : 4.176 [eur]
Literature :
Piston-engined airliners page 41
Praktisch handboek vliegtuigen deel 2 page 277
Tupolev ANT-9 | Bureau of Aircraft Accidents Archives (baaa-acro.com)
Tupolev ANT-9 / PS-9 - passenger (aviastar.org)
Tupolev ANT-9 / PS-9 (all-aero.com)
Tupolev ANT-9 : Tupolev (valka.cz)
Microsoft Word - tupolev.docx (airhistory.net)
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 :
