OPENFOAM VALIDATION CASES
Three element high-lift airfoil - MDA 30P-30N
In this case, we compute the flow around the multi-element airfoil 30P-30N. The Reynolds number is 5 000 000, the airfoil's angle of attack is 0 degrees, we use the Spalart-Allmaras turbulence model, and we consider air as an incompressible flow. We also compare the numerical results obtained with OpenFOAM, against the experimental results found in the literature.
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| AOA | \( c_l \) experimental | \( c_l \) OpenFOAM | Percent Error (%) |
|---|---|---|---|
| \( 0^{\circ} \) | 2.167089 | 2.237588 | 3.253205 |
| AOA | \( c_d \) experimental | \( c_d \) OpenFOAM | Percent Error (%) |
|---|---|---|---|
| \( 0^{\circ} \) | 0.033243 | 0.034598 | 4.076435 |
warning The experimental values were extracted from plots illustrated in the references below.
We can not guarantee the accuracy or precision of this information.
References:
Prediction of high lift: review of present CFD capability. Progress in Aerospace Sciences, 38:145-180. 2002.
Comparative results from a CFD challenge over a 2D three-element high-lift airfoil. NASA Technical Memorandum 112858.
Numerical study to assess sulfur hexafluoride as a medium for testing multi-element airfoils. NASA Technical Paper 3496.
