Problem 1: Carbon dioxide flows isentropically at therate of 1 kg/s through a
convergent-divergent nozzle. The stagnation temperature is 310 Kand the stagnation
pressure is 1400 kPa. If the exit pressure is 101.3 kPa, determinea) throat area, b) exit
Mach number and c) exit velocity. Assume sonic (M =1) conditions atthroat.
(d) plot using MS excel variation of: total temperature, totalpressure, total density,
density, temperature, Mach number, velocity, speed of sound alongthe centre line of
Problem 4: A solid-propellant rocket has the followingdata: Combustion chamber
temperature = 2600 K, Combustion chamber pressure = 20 MPa. Thecombustion
gasses flow isentropically through a convergent-divergent nozzlewith Throat
diameter = 46 mm, The Exhaust gas constant R = 400 J/(kg · K) withGas specific
heat ratio γ = 1.2. The Exit pressure = 100 kPa. Calculate: ExitMach number,
velocity, and mass flow rate.
