This python code is developed by Sreemannarayana Ikkurthi, as a part of course notes for the course 15AES302: Aerodynamics II, in the year 2019-20
In support of Dr. Rajesh Senthil Kumar T., Assistant Professor,
Department of Aerospace Engneering, Amrita Vishwa Vidyapeetham.
Analyse any airfoil from UIUC database in xfoil and obtain cp and polar values
The Super_xfoil folder is the python module for finding cp and polar values for different flow parameters
Database folder consists of all the airfoils in UIUC airfoil data files in .dat or .DAT format.
Create a Results folder, it consists of all the output files from xfoil.
Xfoil folder consists of xfoil program.
Example.ipynb demonstrates some example functions of Super_xfoil
The code consists of a class and several functions for analysing an airfoil in xfoil program.
The code by default selects a random airfoil from the UIUC database and apply spline to upper and lower surface of airfoil and produce required number of points for analysis. These new coordinates are analysed in xfoil with the given input variables.
The INPUTS section contains pts, Re, Mach, N_crit, Alpha variables
pts = No. of points for spline
Re = Reynolds number
Mach = Mach number
N_crit = Critical boundary layer interaction
Alpha = Angle of attack
database_path = path to database folder
xfoil_path = path to xfoil folder
results_path = path to results folder
code_path = path to jupyter notebook file
If any specific airfoil is to be analysed then it can be entered to foil variable in THE CODE section.