A solid rocket motor has a chamber diameter d = 12 cm and a nozzle exit diameter d = 9 cm. The density of the propellant is p, = 1,750 kg / m² and the average regression rate in the combustion chamber is V, = 1.2 cm/s (it burns over the entire cross-sectional area of the combustion chamber a linear 1.2 cm/s of propellant, imagine the red line below moving 1.2 cm per second and how much propellant with that pass over in that time). The exhaust gases have a pressure of p. = 11 kPa, a temperature of T, = 1,975°C, and a gas constant R-400- Find the velocity at the exit of the kg-K nozzle.
A solid rocket motor has a chamber diameter d = 12 cm and a nozzle exit diameter d = 9 cm. The density of the propellant is p, = 1,750 kg / m² and the average regression rate in the combustion chamber is V, = 1.2 cm/s (it burns over the entire cross-sectional area of the combustion chamber a linear 1.2 cm/s of propellant, imagine the red line below moving 1.2 cm per second and how much propellant with that pass over in that time). The exhaust gases have a pressure of p. = 11 kPa, a temperature of T, = 1,975°C, and a gas constant R-400- Find the velocity at the exit of the kg-K nozzle.
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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Transcribed Image Text:Problem 2:
A solid rocket motor has a chamber diameter d=12 cm and a nozzle exit diameter d₂ = 9 cm. The
density of the propellant is p, = 1,750 kg / m³ and the average regression rate in the combustion
chamber is V₁ = 1.2 cm/s (it burns over the entire cross-sectional area of the combustion chamber a
linear 1.2 cm/s of propellant, imagine the red line below moving 1.2 cm per second and how much
propellant with that pass over in that time). The exhaust gases have a pressure of p. = 11 kPa, a
temperature of T, = 1,975°C, and a gas constant R = 400 Find the velocity at the exit of the
kg-K
nozzle.
Te
Pe
1.2 cm/s
A₁
-De
V₂
Pe
Te
Pe
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