Propellant Exit section De = 18 cm Pe = 90 kPa V = 1150 m/s Te = 750 K Combustion: 1500 K, 950 kPa Propellant

Elements Of Electromagnetics
7th Edition
ISBN:9780190698614
Author:Sadiku, Matthew N. O.
Publisher:Sadiku, Matthew N. O.
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The solid- propellant
rocket in Fig. P3.35 is self-contained and has no entrance ducts.
Using a control volume analysis for the conditions shown in
Fig. P3.35, compute the rate of mass loss of the propellant,
assuming that the exit gas has a molecular weight of 28.

Propellant
Exit section
De = 18 cm
Pe = 90 kPa
V = 1150 m/s
Te = 750 K
Combustion:
1500 K, 950 kPa
Propellant
Transcribed Image Text:Propellant Exit section De = 18 cm Pe = 90 kPa V = 1150 m/s Te = 750 K Combustion: 1500 K, 950 kPa Propellant
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