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Sikorsky Ilya Mourometz V
role : heavy bomber
first flight : operational : February 1915
country : Russia
design :
production : 80 aircraft
general information :
On 13 May 1913 the Russki Vitaz flew, the world's first four-engined airplane. This aircraft, also called Le Grand, was designed by Igor Sikorsky and G.I. Lavrov. From this they developed an even larger four-engined biplane, named Ilya
Murometz, after a legendary Russian hero. It had four 100 hp Argus engines and a wingspan of 31m and was January 1914 ready.
On 12 February 1914, this airplane established a striking record. It flew for five hours with 16 passengers and a dog on board, at an altitude of 2000 meters above Moscow.
The Air Force ordered 10 of a military version. This was increased at the outbreak of the war up to 80 aircraft. Five versions were built, they differed mainly in the type of engine installed. The engines had to come from abroad and were often delayed and the engines available had to be installed. The most used engines were Salmson, Sunbeam, Argus and Renault. The Murometz V was a lighter version with better performance.
On 15 February 1915, the first bomb attack was performed with the Murometz from a base at Jablonna in Poland. Until the revolution in 1917, the Ilya Murometz flew some 400 operational flights and during this period only 2 aircraft were lost !
The C-type even had a place for a tail-gunner in the tail! Like the big bombers in WW2 had.
users : Russia
crew : 5
armament : 5 movable 7.70 [mm] (0.303 in) Lewis machine-guns
engine : 4 Sunbeam Crusader liquid-cooled 8 -cylinder V-engine 135 [hp](99.3 KW)
dimensions :
wingspan : 29.8 [m], length : 17.1 [m], height : 4.72[m]
wing area : 125.0 [m^2]
weights :
max.take-off weight : 4589 [kg]
empty weight operational : 3150 [kg] bombload : 521 [kg]
performance :
maximum speed : 110 [km/u] op 1981 [m]
service ceiling : 2900 [m]
endurance : 5.0 [hours]
estimated action radius : 248 [km]
description :
4˝-bay biplane with fixed underwing 4 -wheel landing gear and tail strut
upper wingtips supported by slanted struts
two spar upper and lower wing
engines, landing gear and bombs attached to the wings ,fuel in the fuselage
airscrew :
four fixed pitch 2 -bladed pusher airscrews with max. efficiency :0.63 [ ]
estimated diameter airscrew 3.04 [m]
angle of attack prop : 11.21 [ ]
fine pitch
reduction : 0.61 [ ]
airscrew revs : 1292 [r.p.m.]
pitch at Max speed 1.42 [m]
blade-tip speed at Vmax and max revs. : 208 [m/s]
calculation : *1* (dimensions)
mean wing chord : 2.27 [m]
calculated wing chord (rounded tips): 2.40 [m]
wing aspect ratio : 13.14 []
estimated gap : 2.31 [m]
gap/chord : 1.02 [ ]
seize (span*length*height) : 2405 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 9.9 [kg/hr]
fuel consumption(cruise speed) : 84.3 [kg/hr] (115.0 [litre/hr]) at 64 [%] power
distance flown for 1 kg fuel : 1.17 [km/kg]
estimated total fuel capacity : 653 [litre] (478 [kg])
calculation : *3* (weight)
weight engine(s) dry : 880.0 [kg] = 2.22 [kg/KW]
weight reduction gear : 19.9 [kg]
weight 76 litre oil tank : 6.5 [kg]
oil tank filled with 3.0 litre oil : 2.7 [kg]
oil in engine 22 litre oil : 19.9 [kg]
fuel in engine 3 litre fuel : 2.0 [kg]
weight 49 litre gravity patrol tank(s) : 7.3 [kg]
weight radiator : 56.9 [kg]
weight exhaust pipes & fuel lines 17.4 [kg]
weight cowling 4.0 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 76.0 [kg]
total weight propulsion system : 1106 [kg](24.1 [%])
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fuselage skeleton (wood gauge : 10.90 [cm]): 520 [kg]
bracing : 62.7 [kg]
fuselage covering ( 55.2 [m2] doped linen fabric) : 17.7 [kg]
weight controls + indicators: 10.9 [kg]
weight seats : 15.0 [kg]
weight other details, lighting set, etc. : 17.1 [kg]
weight bomb storage : 36.5 [kg]
weight bomb sight : 1.0 [kg]
weight four 151 [litre] main fuel tanks empty : 48.3 [kg]
weight interior + equipment + fuel lines: 104 [kg]
total weight fuselage : 833 [kg](18.2 [%])
***************************************************************
weight wing covering (doped linen fabric) : 80 [kg]
total weight ribs (165 ribs) : 273 [kg]
weight engine mounts : 20 [kg]
load on front upper spar (clmax) per running metre : 692.8 [N]
load on rear upper spar (vmax) per running metre : 390.5 [N]
total weight 8 spars : 195 [kg]
weight wings : 548 [kg]
weight wing/square meter : 4.38 [kg]
weight 20 interplane struts & cabane : 153.2 [kg]
weight cables (178 [m]) : 62.9 [kg] (= 353 [gram] per metre)
diameter cable : 7.6 [mm]
weight fin & rudder (10.3 [m2]) : 46.7 [kg]
weight stabilizer & elevator (14.1 [m2]): 62.5 [kg]
total weight wing surfaces & bracing : 893 [kg] (19.5 [%])
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weight machine-gun(s) : 63.5 [kg]
weight pivot mounting mg :25.0 [kg]
weight armament : 88 [kg]
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wheel pressure : 1147.2 [kg]
weight 4 wheels (810 [mm] by 125 [mm]) : 93.6 [kg]
weight tailskid : 7.0 [kg]
weight undercarriage with axle 106.9 [kg]
total weight landing gear : 207.6 [kg] (4.5 [%]
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calculated empty weight : 3128 [kg](68.2 [%])
weight oil for 6.0 hours flying : 59.6 [kg]
weight cooling fluids : 85.8 [kg]
weight 25 drums empty : 5.2 [kg]
weight ammunition (1175 rounds) : 45.1 [kg]
weight automatic pistol with spare magazines : 1.2 [kg]
*******************************************************************
calculated operational weight empty : 3319 [kg] (72.3 [%])
published operational weight empty : 3150 [kg] (68.6 [%])
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" "
weight crew : 405 [kg]
weight fuel for 2.0 hours flying : 169 [kg]
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operational weight : 3893 [kg](84.8 [%])
bomb load : 521 [kg]
operational weight bombing mission : 4414 [kg]
fuel reserve : 175 [kg] enough for 2.08 [hours] flying
operational weight fully loaded : 4589 [kg] with fuel tank filled for 72 [%]
published maximum take-off weight : 4589 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (Take-off) : 11.55 [kg/kW]
total power : 397.2 [kW] at 2100 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 0.9 [g] at 1000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.3 [g]
design flight time : 3.50 [hours]
design cycles : 257 sorties, design hours : 900 [hours]
wing loading (MTOW) : 360 [N/m^2]
wing stress (3 g) during operation : 237 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.06 ["]
max. angle of attack (stalling angle) : 10.02 ["]
angle of attack at max. speed : 5.82 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° :0.10 [ ]
lift coefficient at max. angle of attack : 1.04 [ ]
lift coefficient at max. speed : 0.65 [ ]
induced drag coefficient at max. speed : 0.0136 [ ]
drag coefficient at max. speed : 0.0978 [ ]
drag coefficient (zero lift) : 0.0842 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 79 [km/u]
landing speed at sea-level (OW without bombload): 94 [km/hr]
min. drag speed (max endurance) = minimum speed*1.1 at cruise height : 95 [km/hr] at 1981 [m] (power:51 [%])
min. power speed (max range) : 95 [km/hr] at 1981 [m] (power:51 [%])
cruising speed : 99 [km/hr] op 1981 [m] (power:55 [%])
design speed prop : 104 [km/hr]
maximum speed : 110 [km/hr] op 1981 [m] (power:71 [%])
climbing speed at sea-level (without bombload) : 218 [m/min]
calculation : *9* (regarding various performances)
take-off distance at sea-level : 172 [m]
lift/drag ratio : 9.59 [ ]
max. practical ceiling : 3975 [m] with flying weight :3396 [kg]
practical ceiling (operational weight): 3325 [m] with flying weight :3893 [kg]
practical ceiling fully loaded (mtow- 1 hour fuel) : 2550 [m] with flying weight :4505 [kg]
published ceiling (2900 [m]
climb to 1500m (without bombload) : 8.06 [min]
max. dive speed : 301.0 [km/hr] at 1550 [m] height
load factor at max. angle turn 1.56 ["g"]
turn radius at 500m: 75 [m]
time needed for 360* turn 15.9 [seconds] at 500m
calculation *10* (action radius & endurance)
operational endurance : 4.08 [hours] with 5 crew and 521 [kg] bombload and 71.8 [%] fuel
published endurance : 5.00 [hours] with 5 crew and possible useful (bomb) load : 443 [kg] and 88.1 [%] fuel
action radius : 496 [km] with 5 crew and 20[kg] photo camera/radio transmitter or bombload
max range theoretically with additional fuel tanks for total 1685 [litre] fuel : 1450 [km]
useful load with action-radius 250km : 439 [kg]
production : 43.45 [tonkm/hour]
oil and fuel consumption per tonkm : 2.17 [kg]
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Literature :
warplanes WOI page 68td, 70
bomber 1914-1939 page 12
oorlogsvliegtuigen 1914-1918 page 123
praktisch handboek vliegtuigen deel 1 page 216,217
Bombers 1914-19 page 90,91
Jane’s fighting aircraft WWI page 216f
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.
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(c) B van der Zalm 21 August 2019 contact : info.aircraftinvestigation@gmail.com python 3.7.4