I am predicting the external flow around airfoil with high mach number (>0.8), in which cases shock is supposed to occur. I am just wondering how can I identify it and how to show it in my results. thanks a lot. anne

Just plot the pression distribution...if your mesh is fine enough you will see the shock as a sudden change in pressure...

thanks,

do you mean just pressure or total pressure. I think total pressure seems more reasonable, what's your opinion. anne

Depends on what you want...for example if you want to show the non-isentropic behaviour and then the loss of total pressure plot this one... Everything depends on what you need to show...

A numerical Schlieren image is also nice. Plot contours of d(rho)/dx and use an inverse grayscale colormap (tweak the range to show the shock nicely).

This is the pressure gradient which can also be output to the res file. I can't recall if it is output by default (I think it is), but if it isn't you can enable output of variable operators from the output control panel in CFX-Pre. This will make you shock waves should show up nicely.

You can also create isosurfaces of Mach Number equal to one.

-CycLone

thank you all so much. I am trying your ways. anne