Projet 5 : Interpolation and integration methods / Cubic splines and surface interpolation

  • Slides du projet 5
  • Début du projet: Mercredi 10 Avril
  • Fin du projet: Dimanche 28 Avril à 23h59
  • Additional resource can be found in Chapter 7 and 8 of Methodes Numeriques, Algorithmes, analyse et application, available on moodle.

This project is evaluated in english. Everything will have to be written in english, from code comments to the report. Rules are a bit different for the report and we recommend to refer the english guidelines

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.

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.