|December 4, 2012, 04:38||
fluent internal nozzle flow
Join Date: Oct 2012
Posts: 9Rep Power: 6
Hello, I need help setting up the physics for this problem in fluent.
I have a 15 degree conic nozzle which I have created the geometry, and meshed (see attached) and named edges for the inlet and outlet.
Total Pressure = 2.5 MPa
Total Temperature = 2500K
exit mach should be 3.0
here is what I used:
Density-Based Solver : selected because was originally designed for high-speed compressible flows.
2D Space: Planar
energy equation: on energy equation is coupled to the continuity and momentum equations
Viscous model: inviscid
Air - Set density to ideal gas
Cell Zone Conditions
Surface_Body Operating pressure set to 0 Pa
inlet: type pressure-inlet, Gauge total pressure:2500000 Pascal, Gauge Total Temperature 2500 K constant
outlet: type pressure-outlet, Gauge total pressure: 0 Pa, 300K
Formulation:Implicit ,Flux type: Roe-FDS
Spatial Discretization: Least squares cell based
Second order upwind
So... I ran calculation with solution steering, 1000 iterations, flow type supersonic, use fmg initialization
and well it does not look as I had expected. what should I do instead so that I have mach=1 at the inlet, and so that it expands to mach 3 at the exit. the geometry was determined by method of characteristics to do this with the input data.
|Thread||Thread Starter||Forum||Replies||Last Post|
|calculate a nozzle flow using rhoCentralFoam||hg2lf||OpenFOAM||0||October 25, 2012 21:26|
|What the differences flow equation of Fluent 6.3 and Fluent 12.1||opehterinar81||FLUENT||0||August 19, 2011 11:55|
|UDF for transient pressure inlet, mass flow check at nozzle exit and volumetric heat||kokoory||FLUENT||0||August 17, 2011 02:07|
|analyze a cd nozzle with fluent which designed by MOC||mehrzad||Main CFD Forum||0||July 6, 2011 04:33|
|compressible flow in a counterflow nozzle||d.vamsidhar||FLUENT||0||November 24, 2005 02:45|