A rocket is designed to produce 5 MN of thrust at sea level (assume ambient pressure of 0.1 MPa). The pressure in the combustion chamber is 7 MPa and temperature 2800 K. If the working fluid is assumed to be an ideal gas at room temperature with properties of N2 gas at room temperature (molecular weight 28 kg/kmole). Determine specific impulse, mass flow rate, characteristics velocity and throat diameter. (Take R=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 0.1 MPa). The pressure in the combustion chamber is 7 MPa and temperature 2800 K. If the working fluid is assumed to be an ideal gas at room temperature with properties of N2 gas at room temperature (molecular weight 28 kg/kmole). Determine specific impulse, mass flow rate, characteristics velocity and throat diameter. (Take R=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 0.1 MPa). The pressure in the combustion chamber is 7 MPa and temperature 2800 K. If the working fluid is assumed to be an ideal gas at room temperature with properties of N2 gas at room temperature (molecular weight 28 kg/kmole). Determine specific impulse, mass flow rate, characteristics velocity and throat diameter.
(Take R=8314 J/kmole-K, specific heat ratio 1.4 and nozzle exit pressure as 0.1 MPa)
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