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After burning increases the thrust of

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Rocket engines are used for

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In rocket propulsion, the oxygen for combustion of its fuel is taken from

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Which of the above statements are correct for change in properties across normal shock wave?

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Turbo prop-engine has the following additional feature over the turbojet:

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Across a normal shock

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What is the correct statement regarding normal shock wave in a gas?

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In Rayleigh flow at subsonic Mach numbers, heat addition

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In a Rayleigh flow of subsonic compressible flow heating causes

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Normal shock wave occurs in a one dimensional steady

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The static temperature is

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Across the normal shock in a flow

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A normal shock wave cannot occur in convergent portion of

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In a compressible fluid flow field, the Mach number indicates the ratio of

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Which of the following statements are correct for turbo-prop powered aircrafts?

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Then propulsive efficiency is

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The air fuel ratio at this altitude will be

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Which of the following statements are correct for rockets?

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In an adiabatic flow with friction through a constant area duct, the following phenomenons are predicted:

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Fanno line flow is a flow a constant area duct

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