Turbulent flow at low Mach number
I am trying to simulate the turbulent flow around airfoil NACA0012 at low Mach number (say M=0.15) and Re=6e6 in order to perform a shape optimization, then I also need adjoint simulation (impossible with the incompressible formulation, is it right?).
Up to now, I don't have a satisfying enough solution in terms of pressure distribution. I have some questions:
Thank you in advance,
Referring to your last tweet, can you please give me some information about the settings used to have that results?
I am trying to reproduce the same case, but the pressure distribution has a strange behavior near leading edge, as you can see from the Cp plot I attach.
Could you please download the last version of the code (it contains some relevant improvements with respect the previous one)
after unzipping the code you will find a folder called NACA0012_RANS with the files that we have used for the compressible and incompressible validation.
Hi Francisco and thanks for the new version of the solver.
I ran it and both the compressible and incompressible cases work well.
The point is that I try to solve the adjoint problem (either compressible or incompressible), I can not run it and I get this error:
Thanks a lot,
Could you please check that you are using the same spatial discretization for both the flow and adjoint problems in the config file (i.e. use either JST or ROE-2ND_ORDER for both CONV_NUM_METHOD_FLOW and CONV_NUM_METHOD_ADJ)? Could you also please check that they are both using the same type of time integration (i.e. both EULER_IMPLICIT for instance)?
In general, you are not required to use the same scheme, however we recently discovered a small issue in the config options which will be fixed in the next release. For now, this should fix your problem, I think.
I write a post here but then I searched the forum and its already been solved. so can anyone delete this post for me pls? thanks.
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