[Ryuzaki]

Hello,

I am modeling cavity flow via 0.85 Mach and 6.5 million Re conditions. I want to calculate the aerodynamic forces (Fx, Fy, Fz) on the rear wall of the cavity. In this context, I am conducting my studies using both Fluent and CFX.

I am using the same mesh for both software. However, the results I obtained with Fluent and CFX are quite different from each other. Where do you think the problem might be?

I have specified my boundary conditions below.

Fluent

Operating pressure = 0
Inlet = pressure far field, 0.85 Mach, gauge pressure = 50000 Pa
Outlet = pressure far field, 0.85 Mach, gauge pressure = 50000 Pa
Second order discretization schemes
Ideal gas
SST k-w turbulence model

CFX

Reference Pressure = 0
Inlet = Inlet boundary condition-subsonic and velocity components are identified
Outlet = Outlet boundary condition – subsonic- averaged pressure/static pressure = 50000 Pa (I tried both)
Second order discretization schemes
Ideal gas
Shear Stress Transport model

I suspect that the issue lies in the definition of boundary or initial conditions, but I have not yet been able to pinpoint where the problem is.

Thank you,
Ryuzaki.