Flow over 3d wing

rambharath · February 22, 2016, 04:19

Hello,

I'm new to CFD. I'm currently simulating flow over 3D wing (NACA 0018) with no taper. I have used symmetric boundary condition for my flow domain. I'm getting half the value Cl when compared to the experimental results. Does the symmetric boundary condition affect my Cl values or is thr something else that could cause this.

hamed1987 · February 22, 2016, 05:17

Quote:

Originally Posted by rambharath

hello,

i'm new to cfd. I'm currently simulating flow over 3d wing (naca 0018) with no taper. I have used symmetric boundary condition for my flow domain. I'm getting half the value cl when compared to the experimental results. Does the symmetric boundary condition affect my cl values or is thr something else that could cause this.

i think it dosent influence on your data

rambharath · February 22, 2016, 05:43

Thank u hamed. I also tried simulating NACA 0018 airfoil using C mesh. I gave the top and bottom boundary conditions as symmteric.I'm getting the half the values of Cl and Cd.

February 22, 2016, 04:19	Flow over 3d wing	#1
rambharath New Member bram Join Date: Jan 2015 Posts: 10 Rep Power: 11	Hello, I'm new to CFD. I'm currently simulating flow over 3D wing (NACA 0018) with no taper. I have used symmetric boundary condition for my flow domain. I'm getting half the value Cl when compared to the experimental results. Does the symmetric boundary condition affect my Cl values or is thr something else that could cause this.

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February 22, 2016, 05:43		#3
rambharath New Member bram Join Date: Jan 2015 Posts: 10 Rep Power: 11	Thank u hamed. I also tried simulating NACA 0018 airfoil using C mesh. I gave the top and bottom boundary conditions as symmteric.I'm getting the half the values of Cl and Cd.