Adjoint simulation
Dear All,
I have downloaded the last version of the solver from svn (here) and I have tried to solve the attached case (NACA0012). I have tested 2 cases: 1. Mach = 0.15, with incompressible formulation - the direct solution works very well - the adjoint simulation fails 2. Mach = 0.8, compressible - the direct solution works very well - the adjoint simulation seems to work Why this happen? Haven't you tested the adjoint solution for low Mach numbers? Thanks a lot, Samuele |
Hi Samuele,
Please check the post I left over in this thread on the topic: http://www.cfd-online.com/Forums/su2...ch-number.html. Hope this helps! T |
Hi everybody,
I discovered that the problem with my mesh was related to elements near leading edge which didn't follow the curvature of the surface of the airfoil. Now results are very good. I would also like to obtain adjoint solutions: both with drag and lift objective function. In this case the ROE-2ND discretization gave me strange results (attached below); switching to JST, the solution seems to be better (both cases had been ran with drag obj function). Problems arise when I want the adjoint solution with lift objective function; the solution is enormously slow (you can compare the residual.vs.iterations in both cases in the figures attached below). Then I have some questions:
http://dl.dropbox.com/u/27047350/Adjoint.zip thank you in advance, Roberto |
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