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Step 7: Refine Mesh

Before we can make any conclusion about the accuracy of our result, we should always make validation check. The most common validation step is grid convergence check.

A finer mesh with four times the original mesh density was created. The lift coefficient was found to be 0.649.

 

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.

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

 

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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