Attempt to simulate compressible flow in a diffusing S-Duct
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Hello, respected community.
I am trying to simulate with SU2 the compressible flow in a S-Duct (test case of S-Duct of Wellborn - see paper by Harloff et al. in https://ntrs.nasa.gov/archive/nasa/c...9920024502.pdf ). Attachment 70173 I assign boundary conditions as follows: 1) inlet (entry to S-Duct): INLET_TYPE= TOTAL_CONDITIONS MARKER_INLET= ( inlet marker, total temp, total pressure, flow_direction_x, flow_direction_y, flow_direction_z ) 2) outlet (exit from S-Duct) MARKER_OUTLET= ( outlet marker, back pressure (static) ) 3) Inner wall of S-Duct - Navier-Stokes adiabatic wall boundary MARKER_HEATFLUX= ( inner_wall_marker, 0.0 ) Numerical method - ROE scheme, limiter of Venkatakrishnan = 0.5, CFL = 0.5. As a result, the calculation does not converge and the condition of mass flow conservation is not satisfied between the entry and exit planes. In addition, at some iteration number, the solver gives a warning: "There are XXX non-physical points in the solution". In case of use Euler wall boundary, the calculation converges and the condition of mass flow conservation is achieved. Maybe someone faced a similar situation - Does anybody have some ideas why the RANS Spalart-Allmaras SU2 diverges for such a standard tes-case for internal flow ? Any help will be kindly appreciate since currently we are unable to resolve that issue. Sincerely yours, Alexander |
Hey Alexander,
I usually ramp the back-pressure for supersonic turbomachinery cases, maybe you can try that out. Thanks, Nitish |
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