# Different Drag coefficient value???

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 November 30, 2018, 12:31 Different Drag coefficient value??? #1 New Member   kaan Join Date: Nov 2018 Posts: 7 Rep Power: 7 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. Last edited by recep911234; December 1, 2018 at 10:32.

 November 30, 2018, 23:12 #2 Senior Member   Lucky Join Date: Apr 2011 Location: Orlando, FL USA Posts: 5,637 Rep Power: 65 All your pics disappeared recep911234 likes this.

 December 1, 2018, 07:16 #3 Senior Member   Behrooz Jamshidi Join Date: Apr 2013 Posts: 110 Rep Power: 12 As a guess, you have not set the reference values in accordance to your problem. recep911234 likes this.

December 1, 2018, 10:29
#4
New Member

kaan
Join Date: Nov 2018
Posts: 7
Rep Power: 7
Quote:
 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

 Tags airfoil 2d, drag coefficient, fluent, lift and drag, naca 0012

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