[sehs15]

the non reflecting boundary is an option in the pressure outlet boundary conditions .. it is used to eliminate pressure waves reflecting from the outlet boundary and treats it like the boundary is set at infinity ... rotor 37 mesh is the same as 67 im just using reasonable aspect ratio as im not refining too much at the walls .. try to solve laminar and tell me what u got

[rvl565]

Just finished with the laminar simulation... reversed flow at the outlet and inlet and a lot of oscillations in the mass flow rate :'(

[sehs15]

what boundary conditions do u use?

[rvl565]

Pressure Inlet and pressure outlet (averaged specification)...

[andrei.cimpoeru]

Hi All

Has anyone got a fluent mesh for the rotor67 ?


Thanks

Andrei Cimpoeru

[MUSohail]

Hello all

i need guidelines and help from you all. I have done Rotor 67 steady state simulation in CFX and found great results and even validated with NASA results. Now i want to do same simulation in Fluent. I imported Nasa Coordinates and mesh it in turbogrid. Now i am having reverse flows in fluent.
Kindly guide me the boundary conditions in fluent, such as inlet and outlet gauge pressure etc.
Please

[MUSohail]

Hello all

i need guidelines and help from you all. I have done Rotor 67 steady state simulation in CFX and found great results and even validated with NASA results. Now i want to do same simulation in Fluent. I imported Nasa Coordinates and mesh it in turbogrid. Now i am having reverse flows in fluent.
Kindly guide me the boundary conditions in fluent, such as inlet and outlet gauge pressure etc.
Please

[MUSohail]

Originally Posted by rvl565

Hi i wanted to use rotor 67 as a test case for fan simulations.
To speed up the process i am using the mesh provided by stanford university ( http://aero-comlab.stanford.edu/vdweide/CGNSFiles/ )

I removed the tip clearance from this mesh, other than that the mesh is the same.

I am using the MRF model. The boundary conditions are:
Pressure inlet: total pressure = 101325 ( 0 reference pressure)
Initial gauge pressure =99825
% intensity =1
length scale =0.01

Pressure outlet: gauge pressure 114500
backflow length scale and intensity the same as inlet

Rotor RPM: -16043

I extended the inlet and outlet by 0.15m to create two stationary zones.

I used the komegaSST model with compressibility effects and curvature correction.
The energy equation has been turned on and used the ideal gas equation for the density.

I get reversed flow at the inlet and outlet.

Please help me correct this problem.

Thanks!

Hello all

i need guidelines and help from you all. I have done Rotor 67 steady state simulation in CFX and found great results and even validated with NASA results. Now i want to do same simulation in Fluent. I imported Nasa Coordinates and mesh it in turbogrid. Now i am having reverse flows in fluent.
Kindly guide me the boundary conditions in fluent, such as inlet and outlet gauge pressure etc.
Please