A rocket is designed to produce 5 MN of thrust at sea level ( assume ambient pressure of 0.1MPa). The pressure in the combustion chamber is 7 MPa and the temperature is 2800 K. If the working fluid is assumed to be an ideal gas with properties of nitrogen gas (N2) at room temperature (molecular weight 28 kg/kmole), determine the following (a) the specific impulse, (b) mass flow rate of the rocket and (c) the characteristic velocity of the rocket. (use universal gas constant = 8314 J/kmole-K; specific heat ratio = 1.4 and nozzle exit pressure as 0.1 MPa ).
A rocket is designed to produce 5 MN of thrust at sea level ( assume ambient pressure of 0.1MPa). The pressure in the combustion chamber is 7 MPa and the temperature is 2800 K. If the working fluid is assumed to be an ideal gas with properties of nitrogen gas (N2) at room temperature (molecular weight 28 kg/kmole), determine the following (a) the specific impulse, (b) mass flow rate of the rocket and (c) the characteristic velocity of the rocket. (use universal gas constant = 8314 J/kmole-K; specific heat ratio = 1.4 and nozzle exit pressure as 0.1 MPa ).
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A rocket is designed to produce 5 MN of thrust at sea level ( assume ambient pressure of 0.1MPa). The pressure in the combustion chamber is 7 MPa and the temperature is 2800 K. If the working fluid is assumed to be an ideal gas with properties of nitrogen gas (N2) at room temperature (molecular weight 28 kg/kmole), determine the following (a) the specific impulse, (b) mass flow rate of the rocket and (c) the characteristic velocity of the rocket.
(use universal gas constant = 8314 J/kmole-K; specific heat ratio = 1.4 and nozzle exit pressure as 0.1 MPa ).
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