charbileigh/Aircraft-Load-Distribution

Background info of the program: This code is created to open a CSV file, then create a matrix of our distances. Then it is bound to go to an extent where it uses the Gaussian elimination method to get the inverse and then multiplying that with the necessary matrix to get the distributed load. Then from there, it needs to integrate the function to get coefficients for the shear and the bending moment, then get the constants, and then this code is going to allow us to know the bending moment of an aircraft wing. furthermore, we will create an output CSV file. From this, we can deduce the mechanical stresses using the correct equation.

Python