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weight and performance calculations for the Sikorsky Russky Vityaz
Sikorsky Russky Vityaz
role : passenger aircraft
importance : ***
first flight : 13 May 1913 at St.Petersburg operational : May 1913
country : Russia
design : Igor Sikorsky and G.I.Lavrov (a naval officer who later would design a synchronizing gear for the Sikorsky S-16)
production : 1 prototype
general information :
First known as “Bolshoi Baltisky” > The great Baltic (Le Grand). It was powered by two 100hp Argus engines and was largely underpowered. Two engines were added and now it was the first aircraft to fly with 4 engines. It was ahead of its time, with dual controls, a spacy closed cabin for crew and passengers with unbreakable glass windows. Sikorsky’s aspirations for the Russky Vityaz proved to be short-lived. While parked on the runway at Krasnoje Selo , near St.Petersburg on 23 June 1913, the aircraft was crushed by an engine that fell off a single-seat Morane aircraft during landing. Sikorsky decided not to repair the seriously damaged Russky Vityaz and began working on his next brainchild — the Ilya Murometz .
users : Sikorsky
crew : 3 passengers : 7
engine : 4 Argus As.I liquid-cooled 4 -cylinder inline engine 100 [hp](74.6 KW)
dimensions :
wingspan : 28.0 [m], length : 20.0 [m], height : 4.0[m]
wing area : 120.0 [m^2]
weights :
max.take-off weight : 4100 [kg]
empty weight operational : 2700 [kg] useful load : 750 [kg]
performance :
maximum speed :85 [km/u] op 200 [m]
cruise speed :76 [km/u] op 200 [m]
service ceiling : 600 [m]
range : 170 [km]
description :
4½-bay biplane with fixed underwing 8 -wheel landing gear and tail strut
upper wingtips supported by slanted struts
two spar upper and lower wing
engines, landing gear and fuel attached to the wings, useful load in the fuselage
airscrew :
four fixed pitch 2 -bladed tractor airscrews with max. efficiency :0.62 [ ]
estimated diameter airscrew 2.80 [m]
angle of attack prop : 9.04 [ ]
fine pitch
reduction : 1.00 [ ]
Early “Le Grand” with 2 engines
airscrew revs : 1350 [r.p.m.]
pitch at Max speed 1.05 [m]
blade-tip speed at Vmax and max revs. : 199 [m/s]
calculation : *1* (dimensions)
wing chord : 2.50 [m]
mean wing chord : 2.32 [m]
calculated wing chord (rounded leading edge tips): 2.36 [m]
wing aspect ratio : 12.09 []
gap : 2.50 [m]
gap/chord : 1.00 [ ]
seize (span*length*height) : 2240 [m^3]
calculation : *2* (fuel consumption)
oil consumption : 6.6 [kg/hr]
fuel consumption(cruise speed) : 83.1 [kg/hr] (113.3 [litre/hr]) at 86 [%] power
distance flown for 1 kg fuel : 0.92 [km/kg] at 300 [m] cruise height, sfc : 323.3 [kg/kwh]
estimated total fuel capacity : 285.89 [litre] (209.56 [kg])
calculation : *3* (weight)
weight engine(s) dry : 560.0 [kg] = 1.88 [kg/KW]
weight 26.9 litre oil tank : 2.29 [kg]
oil tank filled with 2.2 litre oil : 2.0 [kg]
oil in engine 16.6 litre oil : 14.9 [kg]
fuel in engine 2.0 litre fuel : 1.49 [kg]
weight 48.2 litre gravity patrol tank(s) : 7.2 [kg]
weight radiator : 42.7 [kg]
weight exhaust pipes & fuel lines 10.5 [kg]
weight cowling 3.0 [kg]
weight airscrew(s) (wood) incl. boss & bolts : 81.4 [kg]
total weight propulsion system : 723 [kg](17.6 [%])
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The crew could come to the bow and use a search light (for landing in the dark ??)
fuselage skeleton (wood gauge : 10.15 [cm]): 528 [kg]
fuselage width : 1.53 [m]
cabin layout : pitch : 87 [cm] (1+1) seating in 3.5 rows
passenger cabin area : 4.35 [m2]
weight 7.0 windows : 6.30 [kg]
passenger cabin width : 1.43 [m] cabin length : 3.04 [m] cabin height : 1.90 [m]
cabin space : 8.26 [m3]
weight cabin furbishing : 42.00 [kg]
bracing : 80.0 [kg]
fuselage covering ( 75.6 [m2] doped linen fabric) : 23.8 [kg]
weight instruments. : 1.1 [kg]
weight controls : 9.9 [kg]
weight seats : 30.0 [kg]
weight air conditioning : 10 [kg]
total weight fuselage : 732 [kg](17.8 [%])
***************************************************************
weight wing covering (doped linen fabric) : 91 [kg]
total weight ribs (145 ribs) : 244 [kg]
weight engine mounts : 15 [kg]
weight fuel tanks empty for total 238 [litre] fuel : 19 [kg]
load on front upper spar (clmax) per running metre : 696.0 [N]
load on rear upper spar (vmax) per running metre : 375.6 [N]
total weight 8 spars : 236 [kg]
weight wings : 570 [kg]
weight wing/square meter : 4.75 [kg]
weight 20 interplane struts & cabane : 188.7 [kg]
weight cables (182 [m]) : 67.4 [kg] (= 371 [gram] per metre)
diameter cable : 7.8 [mm]
weight fin & rudder (9.1 [m2]) : 44.6 [kg]
weight stabilizer & elevator (13.5 [m2]): 65.0 [kg]
total weight wing surfaces & bracing : 970 [kg] (23.7 [%])
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Can only operate from paved runways
wheel pressure : 512.5 [kg]
weight 8 wheels (560 [mm] by 66 [mm]) : 62.4 [kg]
weight tailskid : 6.5 [kg]
weight undercarriage with axle 137.4 [kg]
total weight landing gear : 206.3 [kg] (5.0 [%]
*******************************************************************
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calculated empty weight : 2631 [kg](64.2 [%])
weight oil for 2.7 hours flying : 17.5 [kg]
weight cooling fluids : 64.4 [kg]
calculated operational weight empty : 2713 [kg] (66.2 [%])
published operational weight empty : 2700 [kg] (65.9 [%])
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" "
weight crew : 243 [kg]
weight fuel for 2.0 hours flying : 166 [kg]
********************************************************************
operational weight empty: 3122 [kg](76.1 [%])
weight 7 passengers : 539 [kg]
weight luggage & freight : 211 [kg]
operational weight loaded: 3872 [kg](76.1 [%])
fuel reserve : 43.4 [kg] enough for 0.52 [hours] flying
possible additional useful load : 185 [kg]
operational weight fully loaded : 4100 [kg] with fuel tank filled for 100 [%]
published maximum take-off weight : 4100 [kg] (100.0 [%])
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calculation : * 4 * (engine power)
power loading (Take-off) : 13.75 [kg/kW]
power loading (operational without useful load) : 10.47 [kg/kW]
total power : 298.3 [kW] at 1350 [r.p.m]
calculation : *5* (loads)
manoeuvre load : 0.8 [g] at 1000 [m]
limit load : 2.5 [g] ultimate load : 3.8 [g] load factor : 1.4 [g]
design flight time : 1.78 [hours]
design cycles : 394 sorties, design hours : 700 [hours]
operational wing loading : 255 [N/m^2]
wing stress (3 g) during operation : 161 [N/kg] at 3g emergency manoeuvre
calculation : *6* (angles of attack)
angle of attack zero lift : -1.08 ["]
max. angle of attack (stalling angle) : 10.49 ["]
angle of attack at max. speed : 7.11 ["]
calculation : *7* (lift & drag ratios
lift coefficient at angle of attack 0° :0.10 [ ]
lift coefficient at max. angle of attack : 1.08 [ ]
lift coefficient at max. speed : 0.76 [ ]
induced drag coefficient at max. speed : 0.0204 [ ]
drag coefficient at max. speed : 0.1891 [ ]
drag coefficient (zero lift) : 0.1687 [ ]
calculation : *8* (speeds
stalling speed at sea-level (OW): 71 [km/u]
stalling speed at sea-level (MTOW): 81 [km/u]
landing speed at sea-level: 83 [km/hr]
min. drag speed (max endurance) : 79 [km/hr] at 300 [m] (power:80 [%])
min. power speed (max range) : 79 [km/hr] at 300 [m] (power:80 [%])
cruising speed : 76 [km/hr] op 300 [m] (power:74 [%])
design speed prop : 81 [km/hr]
maximum speed : 85 [km/hr] op 200 [m] (power:97 [%])
climbing speed at sea-level : 128 [m/min]
calculation : *9* (regarding various performances)
take-off speed : 84.0 [km/u]
static prop wash : 89 [km/u]
high wheel pressure, can only take off from paved runways
take-off distance at sea-level : 175 [m]
lift/drag ratio : 6.50 [ ]
climb to 1500m with flying weight 3122 [kg] : 38.42 [min]
published ceiling (600 [m]
practical ceiling (operational weight) : 2138 [m] with flying weight :3122 [kg] line 3385
practical ceiling fully loaded (mtow- 30 min.fuel) : 248 [m] with flying weight :4058 [kg]
turning speed at CLmax : 82.4 [km/u] at 50 [m] height
turn radius at 50m: 59 [m]
time needed for 360* turn 16.3 [seconds] at 50m
load factor at max. angle turn 1.35 ["g"]
calculation *10* (action radius & endurance)
published range : 170 [km] with 3 crew and 959.5 [kg] useful load and 88.1 [%] fuel
range : 363 [km] with 3 crew and 750.0 [kg] useful load and 188.1 [%] fuel
max range theoretically with additional fuel tanks for total 1781.9 [litre] fuel : 1202.6 [km]
useful load with range 500km : 763 [kg]
production : 58.38 [tonkm/hour]
oil and fuel consumption per tonkm : 1.54 [kg]
_
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Literature :
Piston-engined airliners page
Historische vliegtuigen
Wikipedia
Warplanes page 32, 70
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/
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(c) B van der Zalm 01 January 2021 contact : info.aircraftinvestigation@gmail.com python 3.7.4
