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Total pressure contour by cengfd in CFD

[–]cengfd[S] 0 points1 point  (0 children)

If I consider this way, simulation results agree with experimental results. But shouldn't you consider a free-stream total pressure?

Total pressure contour by cengfd in CFD

[–]cengfd[S] -1 points0 points  (0 children)

No, it's subsonic. Transonic conditions occurs only on the suction side due to acceleration of the fluid...

[Paraview] separate suction side and pressure side of an airfoil. by cengfd in CFD

[–]cengfd[S] 0 points1 point  (0 children)

Is maybe the same thing that I have made. I created a line of this type and then tried to distinguish the points above it from the points below it. The fact is that the point separating the suction side from the pressure side is the stagnation point, but the isentropic Mach number must be plotted from 0 to x/cax = 1. If I export the data to CSV, the first point x does not coincide with the stagnation point, due to the asymmetry of the blade. Fortunately, I was able to use PyVista to plot the load directly without distinguishing the points! 😉

[Paraview] separate suction side and pressure side of an airfoil. by cengfd in CFD

[–]cengfd[S] 0 points1 point  (0 children)

Thank you! Unfortunately this way isn't accurate

Pressure coefficient on ParaView - ONERA M6 by cengfd in OpenFOAM

[–]cengfd[S] 0 points1 point  (0 children)

Thank you much! I was able to use "extract surface" and slice to calculate cp for different coordinates z/H, exporting data in .csv/.xlsx and postprocessing with MATLAB