In this case, we decided to take 3 bumps : One on the succion side at 1/3 of airfoil chord, one on the succion side at 2/3 of airfoil chord and one last on the pressure side at 2/3 of airfoil chord. Each deformation is then parametrized thanks to the amplitude αi of the sine bump. Those are sinus functions that will be distributed all over a side of your airfoil, where the maximum of amplitude is located on t1i, with a bump width of t2i.
In this case we decided to use Hicks-Henne sine bumps. You got many different methods to do that (mesh point method, B-splines, PARSEC) but you have to keep in mind that you need a smooth shape at the end of the process defined by as less parameters as possible. In this part you will decide how and where your airfoil shape will change. This first tutorial will be about the early steps of creating a surrogate model, by setting a Design of Experiment (DOE) computed with Scilab and simulated with OpenFOAM. NACA 0012 airfoil (OpenFOAM mesh) and pressure coefficients at alpha = 0 degĪs you may know, an optimization process require a surrogate model in order to make fast design space exploration. Let’s take a simple goal for this study: Minimize the pressure drag over lift ratio Cd/Cl by changing the shape of a NACA 0012 airfoil for a Mach number of 0.15, a Reynolds number of 3e6 and 0 deg of angle of attack.
NACA 0012 AIRFOIL GENERATOR HOW TO
The following study leveraging OpenFOAM and Scilab will be divided into 3 tutorials:Įach part of this tutorial will show you how to set a specific stage of a classical engineering process based on the example of an airfoil shape optimization.
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