A combustor produces gases with a molecular weight of 17 g/mol and temperature of 3400 K. Determine
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A combustor produces gases with a molecular weight of 17 g/mol and temperature of 3400 K. Determine the nozzle throat and exhaust areas required for a thrust of 525 kN and an ideal specific impulse of 275 sec. The ambient pressure is 0.1 MPa, and the specific-heat ratio is 1.4. How much thrust would this rocket develop if the ambient pressure were changed to 0.03 MPa? How much thrust would be developed by a rocket designed to expand to 0.03 MPa if it had the same stagnation conditions, throat area, and propellant?
Related Book For
Thermodynamics An Engineering Approach
ISBN: 978-0073398174
8th edition
Authors: Yunus A. Cengel, Michael A. Boles
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