At a point upstream of the throat in a conv.-div. nozzle, the velocity, pressure and temperature 242 of the air are m/s, kPa, and" ), respectively. If the throat and exit cross- sectional areas of the nozzle are ( m² and m²), respectively. Determine: (a) The max. back pressure to chock the nozzle. (b) The back pressure for the nozzle to be perfectly expanded to the design Mach number. (c) The back pressure such that there is a normal shock wave at the exit plane. (d) The range of back pressure for a subsonic non-isentropic, over expansion, and und expansion flow region.

At a point upstream of the throat in a conv.-div. nozzle, the velocity, pressure and temperature 242 of the air are m/s, kPa, and" ), respectively. If the throat and exit cross- sectional areas of the nozzle are ( m² and m²), respectively. Determine: (a) The max. back pressure to chock the nozzle. (b) The back pressure for the nozzle to be perfectly expanded to the design Mach number. (c) The back pressure such that there is a normal shock wave at the exit plane. (d) The range of back pressure for a subsonic non-isentropic, over expansion, and und expansion flow region.

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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