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Flow over an Airfoil - Panel
Flow over an Airfoil - Panel
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FLUENT Google Analytics
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Verification & Validation

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One of the ways we can verify our data is by refining the mesh. Open up the mesh, and increase the Number of Divisions for Edge Sizing and Edge Sizing 2 to 100. Click Mesh in the Outline window, and in the Details window, expand statistics. The number of elements should now be 40000.



Click here to enlarge

Exit out of the mesher. First, right click Setup and select Reset. Then click in the project schematic. Open up the solver, and solve the simulation using the same solver and boundary conditions (you'll have to input them again), but this time change the number of iterations to 5000. Again, calculate the force coefficients and graph the pressure coefficient.

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To validate our data, we will take a compare the data from actual experiment.

 

Unrefined Mesh

Refined Mesh

Experimental Data

Lift Coeffient

0.6315

0.6670

0.6630

Drag Coefficient

0.0122

0.0063

0.0090

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Click here to see an enlarged image

As we can see from the table and the graph, the CFD matches the data fairly well. There are inaccuracies from factors like such as our assumption that the flow was is inviscid, but we still managed to extract some meaningful information from the simulation.

Go to Exercises

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