1. Consider a rocket that has a chamber stagnation pressure of 2.0 MPa with a bell nozzle that is designed with an exit pressure of 26.5 kPa, which is optimal at approximately 10 km altitude. However, the rocket shall be launched at sea-level (pa = 100 kPa). Using the knowledge you obtained from Compressible Flow, determine whether the conditions are such that it is possible that a (normal) shock enters the nozzle. Show your analysis to justify your answer. Assume ? = 1.4.
Added by Albert M.
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The critical back pressure is the pressure at which the flow at the nozzle exit is sonic (M=1). The critical back pressure can be calculated using the following equation: Pbc = P0 * (2/(γ+1))^(γ/(γ-1)) where P0 is the chamber pressure and γ is the specific Show more…
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