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An ideal rocket engine gives a static thrust of 6670 [N] at 6100 [m] altitude standard atmosphere (T=-26 [°C], P=47 [kPa] abs.) with a chamber pressure of 1,035 x 106 [Pa] (abs) and chamber temperature of 3315 [°C]. Assume k = 1,4 and R = 355 [N-m/kg-K] and that exit pressure is that of surroundings. Determine: 1) The throat and the exit areas 2) The velocity at the throat.

An ideal rocket engine gives a static thrust of 6670 [N] at 6100 [m] altitude standard atmosphere (T=-26 [°C], P=47 [kPa] abs.) with a chamber pressure of 1,035 x 106 [Pa] (abs) and chamber temperature of 3315 [°C]. Assume k = 1,4 and R = 355 [N-m/kg-K] and that exit pressure is that of surroundings. Determine: 1) The throat and the exit areas 2) The velocity at the throat.

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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An ideal rocket engine gives a static thrust of 6670 [N] at 6100 [m] altitude standard atmosphere (T=-26 [°C], P=47 [kPa] abs.) with a chamber pressure of 1,035 x 106 [Pa] (abs) and chamber temperature of 3315 [°C]. Assume k = 1,4 and R = 355 [N-m/kg-K] and that exit pressure is that of surroundings. Determine: 1) The throat and the exit areas 2) The velocity at the throat.
Transcribed Image Text:An ideal rocket engine gives a static thrust of 6670 [N] at 6100 [m] altitude standard atmosphere (T=-26 [°C], P=47 [kPa] abs.) with a chamber pressure of 1,035 x 106 [Pa] (abs) and chamber temperature of 3315 [°C]. Assume k = 1,4 and R = 355 [N-m/kg-K] and that exit pressure is that of surroundings. Determine: 1) The throat and the exit areas 2) The velocity at the throat.
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If atmospheric presure and tempreture whas not given how would you determine it

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