Week 7 - Simulation of a 1D Supersonic nozzle flow simulation using Macormack Method

INTRODUCTION TO THE GIVEN PROBLEM

We consider the steady isoentropic flow through the convergent -divergent nozzle as given in diagram below.

The flow at the inlet to the nozzle comes from the reservoir is large (therotically A→∞">A→∞�→∞0 and hence the velocity is very small (V→0)">(V→0)(�→0) .Thus ,po">po�� and To">To�� are the stagnantation values or total pressure and total temperature,respectively.The flow expands isoentropically to supersonic speeds at the nozzle exit,where the exit pressure,temperature where exit parameters are reperesented with subscript e.

The flow is locally subsonic in the convergent section of the nozzle,sonic at the throat (minimum area) ,and supersonic at the divergent section . The sonic flow (M=1)at the throat means the local velocity at this section is equal to the local speed of the sound.We can repersent the throat values with our own representation either with * or any other.

Some of the useful results obtained.