01: A convergent-divergent nozzle has an exit area to throat area ratio of 2. Air enters the nozzles with a stagnation pressure of 6.5 bar and a stagnation temperature of 93°C. The throat area is 6.25 cm. If there is a normal shock wave standing at a point where M= 1.5, determine the pressure, temperature on either side of the plane of shock and the mach number on the downstream side of the plane. Find also the exit mach number of the nozzle. M2 M<1

01: A convergent-divergent nozzle has an exit area to throat area ratio of 2. Air enters the nozzles with a stagnation pressure of 6.5 bar and a stagnation temperature of 93°C. The throat area is 6.25 cm. If there is a normal shock wave standing at a point where M= 1.5, determine the pressure, temperature on either side of the plane of shock and the mach number on the downstream side of the plane. Find also the exit mach number of the nozzle. M2 M<1

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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