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performance calculations for the BMW 132Dc aircraft engine
BMW 132Dc air-cooled 9 -cylinder radial engine 720 [hp](536.9 KW)
gear-driven supercharger, constant power to height : 2600 [m]
blower ratio : 11.40 [:1] German engine rating : 730.0 [PS]
introduction : 1938 country : Germany importance : ***
applications : Focke Wulf FW200A
normal rating : 720 [hp](536.9 KW) at 2300 [rpm] at 2600 [m] above sea level
take-off power : 780 [hp] (581.6 [KW]) at 2350 [rpm]
reduction : 0.62 , valvetrain : overhead valves, pushrod operated
weight engine(s) dry with reduction gear : 525.0 [kg] = 0.98 [kg/KW]
General information :
fuel system : direct injection fuel type : octane grade no. 87 oil system :
engine starter type :
bore : 155.6 [mm] stroke : 162.0 [mm]
valve inlet area : 37.0 [cm^2] one inlet and one exhaust valve in cylinder head
gasspeed at inlet valve : 44.9 [m/s]
blower speed : 26220 [rpm] , mixture :13.0 :1
compression ratio: 6.50 :1
stroke volume (Vs displacement): 27.720 [litre]
compression volume (Vc): 5.041 [litre]
total volume (Vt): 32.766 [litre]
overall engine diameter: 137.0 [cm]
calculated engine length: 119.50 [m]
specific power : 19.4 [kW/litre]
torque : 2229 [Nm]
engine weight/volume : 18.9 : [kg/litre]
average piston speed (Cm): 12.4 [m/s]
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intake manifold absolute pressure (MAP) at 2600 [m] altitude Pi (ata.) : 1.20 [kg/cm2] (34.75 [inHg])
mean engine pressure (M.E.P.) at 2600 [m] altitude Pm : 10.19 [kg/cm2]
compression pressure at 2600 [m] altitude Pc: 12.45 [kg/cm2]
estimated combustion pressure at 2600 [m] Pe : 49.75 [kg/cm2]
exhaust pressure at 2600 [m] Pu : 4.70 [kg/cm^2 ]
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compression-start temperature at 2600 [m] Tic: 336 [°K] (62 [°C])
compression-end temperature at 2600 [m] Tc: 526 [°K] (253 [°C])
average engine wall temperature at 2600 [m] : 476 [K] (202 [°C])
caloric combustion temperature at 2600 [m] Tec: 2446 [°K] (2173 [°C])
polytroph combustion temperature at 2600 [m] Tep : 2102 [°K] (1829 [°C])
estimated combustion temperature at 2600 [m] Te (T4): 2243 [°K] (1970 [°C])
polytrope expansion-end temperature at 2600 [m] Tup: 1175 [°K] (902 [°C])
exhaust stroke end temperature at 2600 [m] Tu: 1129 [°K] (855 [°C])
*********************************************************************************
calculations for take-off/emergency power at sea level
average piston speed : 12.7 [m/s]
gasspeed at inlet valve : 45.9 [m/s]
intake pressure at sea level for Take-off Pi : 1.30 [kg/cm2] (37.75 [inHg])
rich mixture 11.5 : 1 applied for cooling > carburettor adjustable in flight by the pilot
caloric combustion temperature at sea level Tec: 2105 [°K] (1832 [°C])
insufficient cooling, can run max 2 minutes at this power before overheating
low emergency fact > probably rpm must be lower check
emergency/take off rating at 2350 [rpm] at sea level : 778 [hp]
Thermal efficiency Nth : 0.374 [ ]
Mechanical efficiency Nm : 0.742 [ ]
Thermo-dynamic efficiency Ntd : 0.277 [ ]
design hours : 840 [hr] time between overhaul : 297 [hr]
dispersed engine heat by cooling air : 10772.14 [Kcal/minuut/m2]
** veel warmte ontwikkeling, gevaar van oververhitten !!!
required cooling surface : 16.04 [m2]
weight cooling ribs : 47.97 [kg]
fuel consumption optimum mixture at 2300.00 [rpm] at 2600 [m]: 227.78 [kg/hr]
specific fuel consumption thermo-dynamic : 217 [gr/epk] = 291 [gr/kwh]
estimated specific fuel consumption (cruise power) at 2600 [m] : 326 [gr/kwh]
specific fuel consumption (volume*rpm at 1 atm MAP) at 2300 [rpm] : 336 [gr/kwh]
estimated specific oil consumption (cruise power) : 8 [gr/kwh]
Literature :
Jane’s fighting aircraft WWII page 288
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