What is the maximum velocity if the nozzle in Example 3-2 was designed to expand into a vacuum? If the expansion area ratio was 2000?
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.