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performance calculations for the GE-Snecma CFM56-5A1 aircraft engine

Pivoting-door thrust reversers are installed on the CFM56-5. Noise-reducing  chevrons  can also be seen at the engine's rear.

GE-Snecma CFM56-5A1 turbofan engine of 111.0 [KN] (24953 [lbf]) thrust

introduction : 1988 country : US-France importance : ****

applications : Airbus A320-200

max. rating (take-off) : 111.0 [KN] (24953 [lbf], 11319 [kgf])

weight engine(s) dry : 2270.0 [kg] = 48.90 [N/kg]

General information :

by-pass ratio : 6.00 : 1

overall pressure ratio (OPR) : 31.3 : 1

rpm LP : 5000 [rpm]

rpm HP : 14460 [rpm]

axial flow engine

no water injection

1 fan

LP compressor stages : 3 [ ]

HP compressor stages : 9 [ ]

HP turbine stages : 1 [ ]

LP turbine stages : 4 [ ]

stages : 1+3 + 9 + 1 + 4

turbine inlet temperature : 0 [K]

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

air mass flow : 380 [kg/s]

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

estimated specific fuel consumption (cruise power) :60.8 [kg/KNh]

Literature :

Wikipedia

https://www.airbus.com/en/airport-operations-and-technical-data/aircraft-characteristics

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