In: Mechanical Engineering
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.