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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

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

Elements Of Electromagnetics
Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
ChapterMA: Math Assessment
Section: Chapter Questions
Problem 1.1MA
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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.
Transcribed Image Text: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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