With reference to Prob. 3.68, show that the thrust of a rocket engine exhausting into a vacuum
Question:
Mae = exit Mach number
p0 = stagnation pressure in combustion chamber
Note that stagnation temperature does not enter into the thrust.
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In a vacuum patm 0 the solution to ...View the full answer
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Related Book For 
Differential Equations and Linear Algebra
ISBN: 978-0131860612
2nd edition
Authors: Jerry Farlow, James E. Hall, Jean Marie McDill, Beverly H. West
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