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performance calculations for the Shvetsov Ash-62IR (M-62IR) aircraft engine
Svhetsov Ash-62IR (M-62IR) air-cooled 9 -cylinder radial engine 850 [hp](633.8 KW)
gear-driven supercharger, constant power to height : 4200 [m] blower ratio : [:1]
introduction : 1937 country : USSR importance : *****
applications : Tupolev ANT-35
normal rating : 850 [hp](633.8 KW) at 2100 [rpm] at 4200 [m] above sea level
take-off power : 1000 [hp] (745.7 [KW]) at 2200 [rpm]
reduction : 0.625 , valvetrain : overhead valves, pushrod operated
weight engine(s) dry with reduction gear : 560.0 [kg] = 0.88 [kg/KW]
General information : Development of the Wright R-1820 Cyclone with two-speed
supercharger. First run in 1937. License produced in Poland (till 2017!) and China.
Total more than 40.000 built !!
fuel system : fuel type : octane grade no. 87 oil system :
engine starter type :
bore : 155.5 [mm] stroke : 174.5 [mm]
valve inlet area : 36.9 [cm^2] one inlet and one exhaust valve in cylinder head
gasspeed at inlet valve : 44.3 [m/s]
blower speed : [rpm] , mixture :13.0 :1
compression ratio: 6.40 :1
stroke volume (Vs displacement): 29.870 [litre]
compression volume (Vc): 5.523 [litre]
total volume (Vt): 35.349 [litre]
overall engine diameter: 138.0 [cm]
engine length: 121 [cm]
specific power : 21.2 [kW/litre]
torque : 2882 [Nm]
engine weight/volume : 18.7 : [kg/litre]
average piston speed (Cm): 12.2 [m/s]
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intake manifold absolute pressure (MAP) at 4200 [m] altitude Pi : 1.00 [kg/cm2]
(28.96 [inHg])
mean engine pressure (M.E.P.) at 4200 [m] altitude Pm : 10.11 [kg/cm2]
compression pressure at 4200 [m] altitude Pc: 10.18 [kg/cm2]
estimated combustion pressure at 4200 [m] Pe : 40.66 [kg/cm2]
exhaust pressure at 4200 [m] Pu : 3.92 [kg/cm^2 ]
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compression-start temperature at 4200 [m] Tic: 333 [°K] (60 [°C])
compression-end temperature at 4200 [m] Tc: 520 [°K] (247 [°C])
average engine wall temperature at 4200 [m] : 476 [K] (202 [°C])
caloric combustion temperature at 4200 [m] Tec: 2263 [°K] (1990 [°C])
polytroph combustion temperature at 4200 [m] Tep : 2076 [°K] (1803 [°C])
estimated combustion temperature at 4200 [m] Te (T4): 2139 [°K] (1865 [°C])
polytrope expansion-end temperature at 4200 [m] Tup: 1123 [°K] (850 [°C])
exhaust stroke end temperature at 4200 [m] Tu: 1072 [°K] (799 [°C])
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calculations for take-off/emergency power at sea leve
average piston speed : 12.8 [m/s]
gasspeed at inlet valve : 46.4 [m/s]
rich mixture 11.5 : 1 applied for cooling > carburettor adjustable in flight by the pilot
high combustion pressure > high loads on pistonrod and crankcase > to avoid damage
lower Pin
caloric combustion temperature at sea level Tec: 2097 [°K] (1824 [°C])
insufficient cooling, can run max 2 minutes at this power before overheating
emergency/take off rating at 2200 [rpm] at sea level : 1000 [hp]
Thermal efficiency Nth : 0.371 [ ]
Mechanical efficiency Nm : 0.748 [ ]
Thermo-dynamic efficiency Ntd : 0.278 [ ]
design hours : 1158 [hr] time between overhaul : 404 [hr]
dispersed engine heat by cooling air : 7756.42 [Kcal/minuut/m2]
required cooling surface : 19.58 [m2]
weight cooling ribs : 58.89 [kg]
fuel consumption optimum mixture at 2100.00 [rpm] at 4200 [m]: 186.44 [kg/hr]
specific fuel consumption thermo-dynamic : 216 [gr/epk] = 290 [gr/kwh]
estimated specific fuel consumption (cruise power) at 4200 [m] : 375 [gr/kwh]
specific fuel consumption (volume*rpm at 1 atm MAP) at 2100 [rpm] : 279 [gr/kwh]
estimated specific oil consumption (cruise power) : 14 [gr/kwh]
Literature :
Wikipedia
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 :