A normal shock is positioned in the diverging portion of a frictionless, adiabatic, converging- diverging air flow duct where the cross sectional area is 0.0093 [m²] and the local Mach number is 2.0. Upstream of the shock, the stagnation pressure and temperature are 1379 [kPa] and 394[°C] The duct exit area is 0.014[m²], Determine: a) the exit Mach number b) exit temperature, c) exit pressure d) duct exit mass flow rate and e ) thrust.

A normal shock is positioned in the diverging portion of a frictionless, adiabatic, converging- diverging air flow duct where the cross sectional area is 0.0093 [m²] and the local Mach number is 2.0. Upstream of the shock, the stagnation pressure and temperature are 1379 [kPa] and 394[°C] The duct exit area is 0.014[m²], Determine: a) the exit Mach number b) exit temperature, c) exit pressure d) duct exit mass flow rate and e ) thrust.

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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