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weight and performance calculations for the Kalinin K-5
K-5 CCCP-N532
Kalinin K-5
role : light passenger aircraft
importance : ****
first flight : 18 October 1929 operational : May 1932
country : Russia
design : K.Alexeivitsch Kalinin & I.G.Neman
production : 260 aircraft
general information :
Further development of the K-4. The M-15 engine was unreliable at first, later this
Improved, and about 100 aircraft were fitted with this engine. Some received a
Shetsov M-22 radial engine, this engine was more reliable but the bigger engine gave
more drag and performance decreased.
Later aircraft received the liquid cooled Mikulin M-17F , with this engine empty
weight was higher : 2710 kg and MTOW 4000 kg. It had higher max.speed of 209
km/hr, higher ceiling 5560 m and range 1020km. But the higher power and weights
required strengthening of the wing, and payload was lower.
users : Aeroflot
crew : 2 passengers : 8
powerplant : 1 Bessonov M-15 air-cooled 9 -cylinder radial engine 450 [hp] (335.6 KW)
normal rating without supercharger and with 475 [hp](354.2 KW) available for take-
off
dimensions :
wingspan : 20.5 [m], length : 15.87 [m], height : 4.9 [m]
wing area : 66.0 [m^2]
weights :
max.take-off weight : 3750 [kg]
empty weight operational : 2360 [kg] useful load : 800 [kg]
performance :
maximum speed :187 [km/hr] at sea-level
cruise speed :178 [km/u] op 100 [m]
service ceiling : 4780 [m]
range : 950 [km]
description :
high-winged monoplane with fixed landing gear and tail strut
elliptical wing with no flaps airfoil : unknown
engines, landing gear, fuel and useful load in or attached to the fuselage
construction : fuselage mixed construction covered with aluminium and canvas (rear), wooden wing covered with fabric
airscrew :
fixed pitch 2 -bladed tractor airscrew with max. efficiency :0.69 [ ]
estimated diameter airscrew 2.96 [m]
relative pitch (J) : 0.60 [ ]
power loading prop : 113.37 [KW/m]
theoretical pitch without slip : 2.17 [m]
blade angle prop (fixed) : 17.26 [ ]
reduction : 1.00 [ ]
airscrew revs : 1715 [r.p.m.]
aerodynamic pitch at max. continuous speed 1.77 [m]
blade-tip speed at max.continuous speed : 271 [m/s]
propellor noise in flight : 94 [Db]
calculation : *1* (dimensions)
measured wing chord : 3.78 [m] at 50% wingspan
mean wing chord : 3.22 [m]
calculated average wing chord tapered wing with rounded tips: 3.23 [m]
wing aspect ratio : 6.4 []
seize (span*length*height) : 1594 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 8.4 [kg/hr]
fuel consumption(cruise speed) : 68.2 [kg/hr] (93.0 [litre/hr]) at 65 [%] power
distance flown for 1 kg fuel : 2.61 [km/kg] at 2390 [m] height, sfc : 311.4 [kg/kwh]
estimated total fuel capacity : 564 [litre] (414 [kg])
calculation : *3* (weight)
weight engine(s) dry : 354.0 [kg] = 1.05 [kg/KW]
weight 68.4 litre oil tank : 5.81 [kg]
oil tank filled with 2.5 litre oil : 2.3 [kg]
oil in engine 1.9 litre oil : 1.7 [kg]
fuel in engine 2.3 litre fuel : 1.68 [kg]
weight 39.5 litre gravity patrol tank(s) : 5.9 [kg]
weight Burgess type silencers : 6.7 [kg]
weight starter (E.H.I. - Electric Hand Inertia): 8.2 [kg]
weight airscrew(s) incl. boss & bolts : 33.2 [kg]
total weight propulsion system : 419 [kg](11.2 [%])
***************************************************************
fuselage skeleton (wood gauge : 8.88 [cm]): 427 [kg]
cabin layout : pitch : 87 [cm] (1+1) seating in 4.0 rows
weight toilet : 8 [kg]
weight 2 fire extinguisher : 6 [kg]
weight 10 windows : 9.0 [kg]
weight door : 5.0 [kg]
passenger cabin max.width : 1.29 [m] cabin length : 4.65 [m] cabin height : 1.83 [m]
weight cabin furbishing : 20.6 [kg]
weight cabin floor : 33.3 [kg]
bracing : 31.9 [kg]
fuselage covering ( 47.6 [m2] duraluminium 1.65 [mm]) and canvas : 204.6 [kg]
weight radio transceiver equipment : 7.0 [kg]
weight instruments. : 5.0 [kg]
weight lighting : 2.0 [kg]
weight electricity generator : 2.0 [kg]
weight dual controls + indicators: 22.1 [kg]
weight seats : 50.0 [kg]
weight 525 [litre] main fuel tank empty : 42.0 [kg]
weight air conditioning : 7 [kg]
weight engine mounts & firewalls : 17 [kg]
total weight fuselage : 898 [kg](23.9 [%])
***************************************************************
weight wing covering (doped linen fabric) : 69 [kg]
total weight wooden ribs (95 ribs) : 223 [kg]
total weight 4 wooden spars : 262 [kg]
weight wings : 554 [kg]
weight wing/square meter : 8.39 [kg]
weight cables (82 [m]) : 178.8 [kg] (= 2180 [gram] per metre)
diameter cable : 18.9 [mm]
weight fin & rudder (4.9 [m2]) : 41.7 [kg]
weight stabilizer & elevator (7.4 [m2]): 62.8 [kg]
total weight wing surfaces & bracing : 837 [kg] (22.3 [%])
*******************************************************************
wheel pressure : 1875.0 [kg]
weight 2 wheels (1100 [mm] by 169 [mm]) : 82.2 [kg]
weight tailskid : 8.3 [kg]
weight wheel-brakes : 3.2 [kg]
weight shock absorbers : 4.2 [kg]
weight undercarriage with axle 86.7 [kg]
total weight landing gear : 184.6 [kg] (4.9 [%]
*******************************************************************
********************************************************************
calculated empty weight : 2339 [kg](62.4 [%])
URSS-N410 Orohek
weight oil for 6.4 hours flying : 53.8 [kg]
calculated operational weight empty : 2393 [kg] (63.8 [%])
published operational weight empty : 2360 [kg] (62.9 [%])
***o***
"
weight crew : 162 [kg]
weight fuel for 2.0 hours flying : 136 [kg]
********************************************************************
operational weight empty: 2691 [kg](71.8 [%])
weight 8 passengers : 616 [kg]
weight luggage & freight : 184 [kg]
operational weight loaded: 3491 [kg](93.1 [%])
fuel reserve : 258.7 [kg] enough for 3.80 [hours] flying
operational weight fully loaded : 3750 [kg] with fuel tank filled for 95 [%]
published maximum take-off weight : 3750 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (Take-off) : 11.18 [kg/kW]
power loading (operational without useful load) : 8.02 [kg/kW]
total power : 335.6 [kW] at 1715 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 2.7 [g] at 1000 [m]
limit load : 3.0 [g] ultimate load : 4.5 [g] load factor : 1.9 [g]
K-5 with a Shetsov M-22 engine ?
design flight time : 3.74 [hours]
design cycles : 4393 sorties, design hours : 16445 [hours]
operational wing loading : 400 [N/m^2]
wing stress (3 g) during operation : 143 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.37 ["]
max. angle of attack (stalling angle) : 12.78 ["]
angle of attack at max. speed : 1.67 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° : 0.11 [ ]
lift coefficient at max. speed : 0.24 [ ]
lift coefficient at max. angle of attack : 1.14 [ ]
induced drag coefficient at max.speed : 0.0040 [ ]
drag coefficient at max. speed : 0.0434 [ ]
drag coefficient (zero lift) : 0.0394 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW loaded : 3682 [kg]): 101 [km/u]
landing speed at sea-level (normal landing weight : 2884 [kg]): 103 [km/hr]
max. rate of climb speed : 117 [km/hr] at sea-level
max. endurance speed : 113 [km/u] min.fuel/hr : 63 [kg/hr] at height : 610 [m]
max. range speed : 161 [km/u] at cruise height : 4267 [m]
cruising speed : 178 [km/hr] at 2390 [m] (power:90 [%])
max. continuous speed : 182.32 [km/hr]
maximum speed : 187 [km/hr] at 100 [m] (power:114 [%])
climbing speed at sea-level (loaded) : 152 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 122.2 [km/u]
emergency/TO power : 475 [hp] at 1762 [rpm]
static prop wash : 146 [km/u]
take-off distance at sea-level gras field : 338 [m]
take-off distance at sea-level over 15 [m] height : 532 [m]
landing run : 129 [m]
lift/drag ratio : 9.74 [ ]
climb to 1000m with max payload : 11.89 [min]
climb to 2000m with max payload : 34.75 [min]
practical ceiling (operational weight empty 2691 [kg] ) : 4600 [m]
practical ceiling fully loaded (mtow- 30 min.fuel:3716 [kg] ) : 2400 [m]
calculation *10* (action radius & endurance)
published range : 950 [km] with 2 crew and 830.5 [kg] useful load and 88.1 [%] fuel
range : 1030 [km] with 2 crew and 800.0 [kg] useful load and 95.5 [%] fuel
range : 1301 [km] with 8.0 passengers with each 10 [kg] luggage and 120.6 [%] fuel
Available Seat Kilometres (ASK) : 10405 [paskm]
max range theoretically with additional fuel tanks total 1740.8 [litre] fuel : 2703 [km]
useful load with range 500km : 1084 [kg]
useful load with range 500km : 8 passengers
production (useful load): 193 [tonkm/hour]
production (passengers): 1421 [paskm/hour]
oil and fuel consumption per tonkm : 0.40 [kg]
fuel cost per paskm : 0.040 [eur]
crew cost per paskm : 0.078 [eur]
__
I=°°°°°/
°
economic hours : 12775 [hours] is less then design hours
time between engine failure : 1930 [hr]
in case of engine failure only option is emergency landing
writing off per paskm : 0.071 [eur]
insurance per paskm : 0.005 [eur]
rigging cost per paskm : 0.034 [eur]
maintenance cost per paskm : 0.296 [eur]
direct operating cost per paskm : 0.489 [eur]
direct operating cost per tonkm : 4.890 [eur]
Literature :
Wikipedia
Piston engined airliners page 41
Praktisch handboek vliegtuigen deel 5 page 157
Kalinin K-5 : Kalinin (valka.cz)
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
CCCP-N562
(c) B van der Zalm 22 January 2022 contact : info.aircraftinvestigation@gmail.com python 3.7.4