Given the conditions (Temperature, Pressure, etc.) of the combustion chamber as well as the ambient conditions and the diameter/area of the throat, the program will:
a) Solve for the nozzle exit area that produces the max amount of thrust.
b) Use the method of characteristics to solve for the shape of said nozzle.
c) Automatically make curvilinear mesh for simulating the nozzle
d) Solves the Euler equations on the mesh using the MacCormack finite volume method.
e) Plots the results for comparison
Great code, but check your boundary conditions. The zero-velocity BC along the top wall is more of a finite-difference BC. Since you're doing a finite-volume formulation, shouldn't those boundary cell velocities be the negatives of those in the first active cell? That way you have zero velocities AT THE WALL. You do have the symmetry plane BC coded correctly for a finite-volume formulation.