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performance calculations for the Argus As.I WWI aero engine
Argus As.I liquid-cooled 4 -cylinder inline engine 100 [hp](74.6 KW)
introduction : 1911 country : Germany importance : **
applications : Sikorsky Russkye Vityaz
normal rating : 100 [hp](74.6 KW) at 1350 [rpm] at 0 [m] above sea level
no reduction, direct drive, valvetrain : one camshaft in the engine block, two overhead valves per cylinder actuated via roller tappets , pushrods and rocker arms
fuel system : single Cudell-G.A.-carburettor oil system :
weight engine(s) dry : 140.0 [kg] = 1.88 [kg/KW]
bore : 140.0 [mm] stroke : 140.0 [mm]
valve inlet area : 25.0 [cm^2] one inlet and one exhaust valve in cylinder head
gasspeed at inlet valve : 27.2 [m/s]
throttle : 88 /100 open, mixture :13.0 :1
calculated compression ratio : 4.90 : 1
stroke volume (displacement): 8.620 [litre]
compression volume (Vc): 2.208 [litre]
total volume (Vt): 10.828 [litre]
engine height : 90 [cm]
engine length: 0.00 [m]
specific power : 8.7 [kW/litre]
torque : 527 [Nm]
engine weight/volume : 16.2 : [kg/litre]
average piston speed (Cm): 6.3 [m/s]
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intake pressure at 0 [m] altitude Pi : 0.91 [kg/cm2]
mean engine pressure (M.E.P.) at 0 [m] altitude Pm : 6.03 [kg/cm2]
compression pressure at 0 [m] altitude Pc: 6.64 [kg/cm2]
estimated combustion pressure at 0 [m] Pe : 26.52 [kg/cm2]
exhaust pressure at 0 [m] Pu : 3.58 [kg/cm^2 ]
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compression-start temperature at 0 [m] Tic: 382 [°K] (109 [°C])
compression-end temperature at 0 [m] Tc: 552 [°K] (278 [°C])
average engine wall temperature at 0 [m] : 476 [K] (202 [°C])
caloric combustion temperature at 0 [m] Tec: 2168 [°K] (1895 [°C])
polytroph combustion temperature at 0 [m] Tep : 2203 [°K] (1930 [°C])
estimated combustion temperature at 0 [m] Te (T4): 2157 [°K] (1884 [°C])
polytrope expansion-end temperature at 0 [m] Tup: 1208 [°K] (935 [°C])
exhaust stroke end temperature at 0 [m] Tu: 1124 [°K] (850 [°C])
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emergency/take off rating at 1571 [rpm] at sea level : 105 [hp]
Thermal efficiency Nth : 0.328 [ ]
Mechanical efficiency Nm : 0.777 [ ]
Thermo-dynamic efficiency Ntd : 0.255 [ ]
design hours : 89 [hr] time between overhaul : 3 [hr]
dispersed heat by cooling fluids at 1350.00 [rpm] at 0 [m]: 22.19 [Kcal/minuut/litre]
** internal heat transfer (a1): 6424.42 [Kcal/minuut/m2)
required cooling surface : 4.63 [m2]
fuel consumption optimum mixture at 1350.00 [rpm] at 0 [m]: 24.47 [kg/hr]
specific fuel consumption thermo-dynamic : 236 [gr/epk] = 316 [gr/kwh]
estimated specific fuel consumption (cruise power) at 0 [m] optimum mixture : 320 [gr/kwh]
estimated sfc (cruise power) at 300 [m] rich mixture : 323 [gr/kwh]
specific fuel consumption at 0 [m] at 1350 [rpm] with mixture :13.0 :1 : 328 [gr/kwh]
estimated specific oil consumption (cruise power) : 22 [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 01 January 2021 contact : info.aircraftinvestigation@gmail.com python 3.7.4
notes :