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A rocket has a nozzle which is expanded from a chamber pressure of 10 MPa to a pressure that is 2/3 of sea level atmospheric pressure. The throat has a diameter of 3 cm and the propellant has a ratio of specific heats of 1.2.
a. Calculate the area ratio of the nozzle.
b. Calculate the thrust when it is operated at sea level.
c. Calculate the thrust when it is operated at vacuum conditions.
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