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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

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.

 

Jul 23 2020 View more View Less

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