This project implements a (somewhat basic) model to represent the air flow around an airfoil, i.e. the cross section of an aircraft’s wing. The goal consists in obtaining a pressure map above and below the wing, so as to approximate the wing’s lift, i.e. its ability to sustain the plane in the air. This is to be done in two steps : first, refine the airfoil into a sufficiently smooth curve, then compute the pressure map using integration methods.
This project is composed of:
The very first step consists in selecting an airfoil in the database of the UIUC Applied Aerodynamics Group. These data may be loaded into Python as arrays of points by using the following file.
Even if the subject is in english, the project should be done in french.
It is mandatory to validate the two preliminary steps correctly, by proving that the implemented functions return the correct results on predefined problems.
Attention will be paid to the algotrithmic complexity of each step of the project.