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
It's running! It's cool.
Hey Man Is there a project report for this
or any kind of detail?
nice job ;)
is this code applicable to design a Hypersonic nozzle for Wind-tunnels ?
hey guys!!! in the code nozzle.m, what is the 'Nozzle width'?????
how did u get the coordinates of the boundary points ??
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Good approach! Does it possible to compute the supersonic flow out of nozzle based on this model?
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.
Well-founded approach to the solution of CFD problem. Well done!
its a good attempt
There was a error on line 229, and is a miss semicolon and it was give dimension error.
Please note that, and thank you very much for the work.
do you have a code for flow characterization through a given 2-d nozzle??
Added CFD capability and improved plots. Added files and zipped them.
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