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performance calculations for the Bessonov M-15 aircraft engine
Bessonov M-15 air-cooled 9 -cylinder radial engine 450 [hp](335.6 KW)
introduction : 1931 country : USSR importance : **
applications : Kalinin K-5 design : A.A.Bessonov and A.P.Ostrovskiy
normal rating : 450 [hp](335.6 KW) at 1715 [rpm] at 0 [m] above sea level
take-off power : 475 [hp] (354.2 [KW]) at 1800 [rpm]
no reduction, direct drive, valvetrain : overhead valves, pushrod operated
weight engine(s) dry : 354.0 [kg] = 1.05 [kg/KW]
General information : design based on the Bristol Jupiter, At first unreliable later
improved
fuel system : fuel type : octane grade no. 72 oil system :
engine starter type :
bore : 146.0 [mm] stroke : 190.5 [mm]
valve inlet area : 39.0 [cm^2] two inlet and two exhaust valves in cylinder head
gasspeed at inlet valve : 32.9 [m/s]
throttle : 90.0 /100 open, mixture :13.0 :1
compression ratio: 5.30 :1
stroke volume (Vs displacement): 28.760 [litre]
compression volume (Vc): 6.675 [litre]
total volume (Vt): 35.379 [litre]
calculated diam. engine : 145 [cm]
calculated engine length: 112.13 [m]
specific power : 11.7 [kW/litre]
torque : 1868 [Nm]
engine weight/volume : 12.3 : [kg/litre]
average piston speed (Cm): 10.9 [m/s]
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intake manifold absolute pressure (MAP) at 0 [m] altitude Pi : 0.89 [kg/cm2] (25.70 [inHg])
mean engine pressure (M.E.P.) at 0 [m] altitude Pm : 6.52 [kg/cm2]
compression pressure at 0 [m] altitude Pc: 7.14 [kg/cm2]
estimated combustion pressure at 0 [m] Pe : 28.50 [kg/cm2]
exhaust pressure at 0 [m] Pu : 3.49 [kg/cm^2 ]
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compression-start temperature at 0 [m] Tic: 365 [°K] (91 [°C])
compression-end temperature at 0 [m] Tc: 538 [°K] (264 [°C])
average engine wall temperature at 0 [m] : 476 [K] (202 [°C])
caloric combustion temperature at 0 [m] Tec: 2166 [°K] (1893 [°C])
polytroph combustion temperature at 0 [m] Tep : 2147 [°K] (1874 [°C])
estimated combustion temperature at 0 [m] Te (T4): 2122 [°K] (1849 [°C])
polytrope expansion-end temperature at 0 [m] Tup: 1166 [°K] (893 [°C])
exhaust stroke end temperature at 0 [m] Tu: 1091 [°K] (818 [°C])
*********************************************************************************
calculations for take-off/emergency power at sea level
average piston speed : 11.4 [m/s]
gasspeed at inlet valve : 34.5 [m/s]
intake pressure at sea level for Take-off Pi : 0.91 [kg/cm2] (26.22 [inHg])
caloric combustion temperature at sea level Tec: 2167 [°K] (1894 [°C])
insufficient cooling, can run max 2 minutes at this power before overheating
emergency/take off rating at 1800 [rpm] at sea level : 475 [hp]
Thermal efficiency Nth : 0.341 [ ]
Mechanical efficiency Nm : 0.781 [ ]
Thermo-dynamic efficiency Ntd : 0.266 [ ]
design hours : 1491 [hr] time between overhaul : 386 [hr]
dispersed engine heat by cooling air : 4062.15 [Kcal/minuut/m2]
required cooling surface : 12.48 [m2]
weight cooling ribs : 35.11 [kg]
fuel consumption optimum mixture at 1715.00 [rpm] at 0 [m]: 114.66 [kg/hr]
specific fuel consumption thermo-dynamic : 226 [gr/epk] = 303 [gr/kwh]
estimated specific fuel consumption (cruise power) at 0 [m] : 309 [gr/kwh]
specific fuel consumption at 0 [m] at 1715 [rpm] with mixture :13.0 :1 : 342 [gr/kwh]
estimated specific oil consumption (cruise power) : 25 [gr/kwh]
Literature :
Soviet Military Thought - Google Boeken
Praktisch handboek vliegtuigen deel 5 page 159
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 22 January 2022 contact : info.aircraftinvestigation@gmail.com python 3.7.4
notes :