1. AeroPy Documentation

This project was elaborated because of the need of optimizing an airfoil according to its aerodynamic and structural performance (conference paper). Contrary to available options such as XFLR5, AeroPy aims to be an open source Python code. It is a quick and easy way to find the aerodynamic pressure and the drag and lift coefficients through the use of MIT’s XFOIL embedded in Python. Contrary to the other libraries, AeroPy does not have a GUI and is intended to be used in Python codes for optimizations or any other process that requires several aerodynamic analysis.

AeroPy is separated in three modules: (it is programmed in such a way that a new module can be easily inserted)

  • xfoil: contains all the functions relating to XFOIL.

  • aero: contains all functions related to aerodynamics, but not related to XFOIL.

  • PyXFOIL: imports all functions and acts as the intersection of all different

    modules

1.1. Code

Created on Sun Aug 16 20:59:22 2015

@author: Pedro

AeroPy.find_3D_coefficients(airfoil, alpha, Reynolds=0, iteration=10, NACA=True, N=10, span=10.0, taper=1.0, chord_root=1, alpha_root=1.0, velocity=1.0)[source]

Calculate the 3D distribution using the Lifting Line Theory.

Parameters:
  • airfoil – if NACA is false, airfoil is the name of the plain filewhere the airfoil geometry is stored (variable airfoil). If NACA is True, airfoil is the naca series of the airfoil (i.e.: naca2244). By default NACA is False.
  • Reynolds – Reynolds number in case the simulation is for a viscous flow. In case not informed, the code will assume inviscid. (Use the aero_module function to calculate reynolds)
  • alpha – list/array/float/int of angles of attack.
  • iteration – changes how many times XFOIL will try to make the results converge. Specialy important for viscous flows
  • NACA – Boolean variable that defines if the code imports an airfoil from a file or generates a NACA airfoil.
  • N – number of cross sections on the wing
  • span – span in meters
  • taper – unidimendional taper (This options is still not 100% operational)
  • chord_root – value of the chord at the the root
  • alpha_root – angle of attack of the chord at the root (degrees)
  • velocity – velocity in m/s