Wolf Dynamics - Multiphysics simulations, optimization, and data analytics


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-4.x, against the experimental results found in the literature.



AOA\( c_l \) experimental\( c_l \) OpenFOAMPercent Error (%)
\( 0^{\circ} \) 2.167089 2.237588 3.253205


AOA\( c_d \) experimental\( c_d \) OpenFOAMPercent 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.



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.

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