Calculate the ideal thrust and the ideal specific impulse

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Reference no: EM131401280

1. For an ideal rocket with a characteristic velocity c∗ = 1500 m/sec, a nozzle throat diameter of 20 cm, a thrust coefficient of 1.38, and a mass flow rate of 40 kg/sec, compute the chamber pressure, the thrust, and the specific impulse.

2. For the rocket unit given in Example 3-2 compute the exhaust velocity if the nozzle is cut off and the exit area is arbitrarily decreased by 50%. Estimate the losses in kinetic energy and thrust and express them as a percentage of the original kinetic energy and the original thrust.

Example 3-2

A rocket operates near sea level with a chamber pressure of p1 = 2.068 MPa or 300 psia, a chamber temperature of 2222 K, and a propellant consumption of m? = 1.0 kg/sec. Take k = 1.30 and R = 345.7 J/kg-K. Calculate the ideal thrust and the ideal specific impulse. Also plot the cross-section area A, the local velocity v, the specific volume V, the absolute temperature T, and the local Mach number M with respect to pressure along the nozzle.

Reference no: EM131401280

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