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determine a the actual thrust b the actual exhaust velocity c the actual specific impulse d the velocity correction factor Assume that the thrust correction factor is 0 985 and the

determine (a) the actual thrust; (b) the actual exhaust velocity; (c) the actual specific impulse; (d) the velocity correction factor. Assume that the thrust correction factor is 0.985 and the discharge correction factor is 1.050.

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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