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.

Principles of Heat Transfer (Activate Learning with these NEW titles from Engineering!)

8th Edition

ISBN:9781305387102

Author:Kreith, Frank; Manglik, Raj M.

Publisher:Kreith, Frank; Manglik, Raj M.

Chapter10: Heat Exchangers

Section: Chapter Questions

Problem 10.19P

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