Problem 1: Carbon dioxide flows isentropically at the
rate of 1 kg/s through a
convergent-divergent nozzle. The stagnation temperature is 310 K
and the stagnation
pressure is 1400 kPa. If the exit pressure is 101.3 kPa, determine
a) throat area, b) exit
Mach number and c) exit velocity. Assume sonic (M =1) conditions at
throat.
(d) plot using MS excel variation of: total temperature, total
pressure, total density,
density, temperature, Mach number, velocity, speed of sound along
the centre line...