Hi Experts Here,
Need you generous help on the issue as the topics says. Bascially, we run a flow simulation for nd2030 airfoil (2D) at Re 10^5. I followed the steps in "Introduction of SolidWorks Simulation 2012" and did some modifications in the running process. What I want to have is accurate enough (say, +-10%) lift and drag coefficients. Some key settings of my simulation are as follows:
Follow simulation in SW2012
2D simulation for nd2030 airfoil
Reynolds number is 10^5 (x-axis velocity is 4.9049 m/s)
No setting for boundary conditions
Increase the area to 400m * 400m * 0.004m (> 200 chords for both x and y axes, z-axis no change)
Use local mesh to enhance the area near to the airfoil (the component for )
I have attached my sld.part file and the wind-tunnel data here. Just analyze C_L first (I know C_d is more difficult and I am not in that step yet), which is 0.04, similar to the result (0.038) given in "Introduction of SolidWorks Simulation 2012" but there is a such big gap when compared with Selig's wind tunnel data (0.25 around). In such case, the simulation result is totally useless to me.
So help me out please!!!! I have tried whatever I can and believe my procedure is generally OK. However, I do hope I did sth wrongly and someone can modify my setting and get the good enough result.
Check some papers online and it sees that Xfoil can predict the C_l C_d pretty well. I think Flow Simulation should be more advanced than Xfoil so supposedly better results can be obtained. I must set sth wrongly.
Look forward to any replies!!!! Waiting online!!!!!!