Displacement and momentum thickness around Naca 0012 in a Transonic Flow
Hi everybody !
I'm simulating flow around a Naca 0012 airfoil with angle of attack 1.25 (degree) and farfield mach number 0.8. The results for displacement thickness and momentum thickness are shown in 2 graphs in following links. http://inspic.com/4412C0D6 http://inspic.com/42B9FFCD In all field, both of thickness are negative. Are they correct ? 
how did you calculate momentum and displacement thickness?

I've created some lines normal to airfoil and then export xvelocity & yvelocity on them. After that with a matlab code, I projected xvelocity & yvelocity on 2 directions: parallel to surface and normal to surface in each point. finally with an integration, i calculated displacements.
displacement thickness = int[ 1  rho * u / rho_inf / u_inf, 0 , inf ] momentum thickness = int[ rho/rho_inf * u / u_inf *( 1  u/ u_inf), 0 , inf ] 
Hi,
Your post is very interesting. I am working on a similar 3D problem and having hard time in getting MOmentum and displacement thickness. I appreciate if you can post the matlab script. I know hoe to create lines and get x and y velocity data from Fluent. Thanks 
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