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#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) ![]() 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 09:32. |
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#2 |
Senior Member
Lucky
Join Date: Apr 2011
Location: Orlando, FL USA
Posts: 5,728
Rep Power: 66 ![]() ![]() ![]() |
All your pics disappeared
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#3 |
Senior Member
Behrooz Jamshidi
Join Date: Apr 2013
Posts: 110
Rep Power: 13 ![]() |
As a guess, you have not set the reference values in accordance to your problem.
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#4 |
New Member
kaan
Join Date: Nov 2018
Posts: 7
Rep Power: 7 ![]() |
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Tags |
airfoil 2d, drag coefficient, fluent, lift and drag, naca 0012 |
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