The repository contains a tool dedicated to optimize an aircraft wing using gradient method. The program has been written in Python 2.7.
The program is dedicated to optimize an aircraft wing of any shape using gradient method. The goal of the optimization is to minimize drag coefficient using wingspan and standard mean chord as decision variables.
The program consists of five files:
Its central point is the wing_optimization.py file - it incorporates the algorithmes responsible for the optimization. A user enters all parameters of a wing into this file and a number of iterations of the optimization procedure into the number_of_iterations.txt file. Two output files - results.txt and results_of_the_last_iteration.txt - provide a user with results of the optimization. The first one contains values of the decision variables in each iteration, while the second one contains the final parameters of the wing. Last but not least, the figures.py file is utilized to plot graphs of some selected parameters like objective function (look at the figure below).
