Problem 1: Carbon dioxide flows isentropically at the rate of 1 kg/s through a convergent-divergent nozzle.

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 of

Problem 4: A solid-propellant rocket has the following data: Combustion chamber
temperature = 2600 K, Combustion chamber pressure = 20 MPa. The combustion
gasses flow isentropically through a convergent-divergent nozzle with Throat
diameter = 46 mm, The Exhaust gas constant R = 400 J/(kg · K) with Gas specific
heat ratio γ = 1.2. The Exit pressure = 100 kPa. Calculate: Exit Mach number,
velocity, and mass flow rate.