last digit 5The Snecma M88 is a French afterburning turbofan engine developed by Snecma (nowknown as Safran Aircraft Engines) for the Dassault Rafale fighter. The following are somepreliminary design data at takeoff conditions.The engine pressure ratio 24.5, bypass ratio 0.3 and total air mass flow rate 60+last digit kg/s.Inlet diffuser: stagnation pressure ratio 0.98.Fan: pressure ratio 1.3, isentropic efficiency 0.89, first-stage hubtip diameters 0.22/0.66 m,0.96.1. The air inlet velocity to the fan is 150 m/s entering axially and the LP-spool rotating speedis 5000 rpm. Draw the velocity triangle and blade shapes. Calculate maximum inletrelative Mach number. Check if there is any shock formation.

The Snecma M88 is a French afterburning turbofan motor created by Snecma for the Dassault Rafale…

Answered: 5, bypass ratio 0.3 and total air mass…

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5, bypass ratio 0.3 and total air mass fle essure ratio 0.98. tropic efficiency 0 89 first-stage bubiti

Elements Of Electromagnetics

7th Edition

ISBN:9780190698614

Author:Sadiku, Matthew N. O.

Publisher:Sadiku, Matthew N. O.

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Question

last digit 5
The Snecma M88 is a French afterburning turbofan engine developed by Snecma (now
known as Safran Aircraft Engines) for the Dassault Rafale fighter. The following are some
preliminary design data at takeoff conditions.
The engine pressure ratio 24.5, bypass ratio 0.3 and total air mass flow rate 60+last digit kg/s.
Inlet diffuser: stagnation pressure ratio 0.98.
Fan: pressure ratio 1.3, isentropic efficiency 0.89, first-stage hubtip diameters 0.22/0.66 m,
0.96.
1. The air inlet velocity to the fan is 150 m/s entering axially and the LP-spool rotating speed
is 5000 rpm. Draw the velocity triangle and blade shapes. Calculate maximum inlet
relative Mach number. Check if there is any shock formation.

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