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performance calculations for the GE-Snecma CFM56-2 aircraft engine

GE-Snecma CFM56-2C1 turbofan engine of 97.5 [KN] (21919 [lbf]) thrust

introduction : 1981 country : US-France importance : ***

applications : Douglas DC-8-71

max. rating (take-off) : 97.5 [KN] (21919 [lbf], 9942 [kgf])

weight engine(s) dry : 2100.0 [kg] = 44.93 [N/kg]

General information :

by-pass ratio : 6.0 : 1

overall pressure ratio (OPR) : 31.3 : 1

rpm LP : 5176 [rpm]

rpm HP : 14460 [rpm]

axial flow engine

no water injection

LP compressor stages : 4 [ ]

HP compressor stages : 9 [ ]

HP turbine stages : 1 [ ]

LP turbine stages : 4 [ ]

stages : 4 + 9 + 1 + 4

turbine inlet temperature : 0 [K]

fan diameter : 173.0 [cm] engine diameter : 191.0 [cm]

air mass flow : 365 [kg/s]

design hours : 692 [hr] time between overhaul : 346 [hr]

estimated specific fuel consumption (cruise power) :64.8 [kg/KNh]

CFM56-2 attached to a DC-8-71 wing

Literature :

CFM International CFM56 - 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 22 October 2022 contact : info.aircraftinvestigation@gmail.com python 3.7.4

notes :