Engineering, 31.05.2021 21:20 alvalynnw

A liquid propellant engine has the following characteristics: chamber pressure of 7 MPa, constant ratio of specific heats of 1.3, and a characteristic velocity of 1600 m/s. The nozzle has the following characteristics: throat area of 0.010 m2 and an expansion ratio of 10. Calculate the following: 1. Thrust coefficient at sea level
2. Specific impulse at sea level
3. Altitude at optimal expansion
4. Thrust coefficient at optimal expansion
5. Mass flux through the throat

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