[recep911234]

Thats my graduated project and i got different values every time to calculate the drag coefficient. On ansys i have a mesh naca0012 airfoil 2d profile which has 247000 nodes and start the analysis on fluent. I work transient flow and these are my parameters to take
This is mesh
Mesh information
In fluent this is my reference values and time, type
Turbulance Models
Solution Method(i solve second order)
This is my calculation page
and the result(Mine)
Result(which i based on) in this image Cdw is the drag coefficient*

Our drag coefficient is different then thesis and i have to figure out this problem. Also lift coefficient is different too but not so much as drag coefficient. What is my wrong(s)? thanks for helping btw.

[LuckyTran]

All your pics disappeared

[CFD-fellow]

As a guess, you have not set the reference values in accordance to your problem.

[recep911234]

Originally Posted by CFD-fellow

As a guess, you have not set the reference values in accordance to your problem.

i set the reference values already and take this values from farfield. i calculate pressure, temperature and set the aoa 5. but its not working, drag coefficient is awkward