The gas entering a rocket nozzle has a stagnation pressure of (1500 mathrm{kPa}) and a stagnation temperature
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The gas entering a rocket nozzle has a stagnation pressure of \(1500 \mathrm{kPa}\) and a stagnation temperature of \(3000^{\circ} \mathrm{C}\). The rocket is traveling in the still Standard Atmosphere at 30,000 m. Find the throat and exit area for a flow rate of \(10 \mathrm{~kg} / \mathrm{s}\). Assume \(k=1.35, R=\) \(287.0 \mathrm{~N} \cdot \mathrm{m} / \mathrm{kg} \cdot \mathrm{K}\). The gas is perfectly, expanded to the ambient pressure.
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Related Book For
Munson Young And Okiishi's Fundamentals Of Fluid Mechanics
ISBN: 9781119080701
8th Edition
Authors: Philip M. Gerhart, Andrew L. Gerhart, John I. Hochstein
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