fluent internal nozzle flow
3 Attachment(s)
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: Physicssetup General DensityBased Solver : selected because was originally designed for highspeed compressible flows. Time: Steady 2D Space: Planar Models energy equation: on energy equation is coupled to the continuity and momentum equations Viscous model: inviscid Materials Air  Set density to ideal gas Cell Zone Conditions Surface_Body Operating pressure set to 0 Pa Boundary Conditions inlet: type pressureinlet, Gauge total pressure:2500000 Pascal, Gauge Total Temperature 2500 K constant outlet: type pressureoutlet, Gauge total pressure: 0 Pa, 300K Solution Methods Formulation:Implicit ,Flux type: RoeFDS Spatial Discretization: Least squares cell based flow 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.:confused: Attachment 17434 Attachment 17435 Attachment 17436 
1 Attachment(s)
re ran with a modified geometry including a convergent seciton... results look more like they should, but is this necessary? :confused:Attachment 17444

All times are GMT 4. The time now is 20:44. 