Hot gases at 2100 K and 14 MPa expand ideally to 0.1 MPa through a rocket nozzle.
Molecular mass = 22 kg/kmol, heat-capacity ratio $\gamma = 1.32$,
Universal gas constant = 8314 J/kmol-K, \(g = 9.8\,\text{m/s}^2\).
Throat area = \(0.1\ \text{m}^2\).
Find the specific impulse (round off to 2 decimals).