Wolf Dynamics - Multiphysics simulations, optimization, and data analytics

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-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.

 

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.


Download here the case file.