RESULTS

Tests and Outcomes

In our testing, we were able to create an airfoil that XFOIL estimates to have a lift to drag ratio of 103 combined over 4 angles of attack, and has a maximum lift to drag ratio of 156.42 at an 11-degree angle of attack. This is very close to and even better than some standard symmetric foils, especially because it can adapt to any Reynolds number perfectly instead of just being a close guess.

We then continued on to more complex fluid dynamics solvers, using SolidWorks flow simulation to check for laminar and turbulent flow in our model. We found that the foil performs much as it did in XFOIL, though with slightly more turbulence as it gets close to 12 degrees, which is to be expected.