The following parameters characterise a liquid-fuelled rocket engine: stagnation pressure P0=100bar; stagnation temperature TO=3300K; nozzle exit diameter DE=1.0m; throat diameter=0.1 m; gas constant R=692 Jkg-1 K -1; ratio of specific heats cp/cV=y=1.25. Estimate the following: static pressure at the exit plane, exit Mach number.

The following parameters characterise a liquid-fuelled rocket engine: stagnation pressure P0=100bar; stagnation temperature TO=3300K; nozzle exit diameter DE=1.0m; throat diameter=0.1 m; gas constant R=692 Jkg-1 K -1; ratio of specific heats cp/cV=y=1.25. Estimate the following: static pressure at the exit plane, exit Mach number.

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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