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| Original Mesh | Fine Mesh | %Dif |
|---|---|---|---|
CL | 0.647 | 0.649 | 0.3% |
We see that the difference is fairly small and concluded that the original mesh obtained grid convergence.
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The modeling result obtained is still off from the literature result. Further validation steps are needed before we can conclude about the accuracy of our model. Other parameter that will affect the validity of our result is the choice of viscous model. We used Another parameter that we should validate is our choice of viscous model in modeling the airfoil. We used inviscid model which basically assumed that the flow inviscid and totally ignore the effect of boundary layer near the airfoil surface. |
Comparisons
With our simulation data, we can now compare the Fluent with experimental data. The summary of result is shown in the table.
CL | Cd | |
FLUENT | 0.647 | 0.00249 |
Experiment | 0.6 | 0.007 |
Theory | - | 0 |
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Reference
The experimental data is taken from Theory of Wing Sections By Ira Herbert Abbott, Albert Edward Von Doenhoff pg. 493
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http://books.google.com/books?id=DPZYUGNyuboC&printsec=frontcover&dq=Theory+of+Wing+Sections&ei=u6a6SZLfBJ6cMtj-iOcL#PPA489,M1 |
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