An aerodynamic shape optimization algorithm for 2D airfoils.

SHAPE PARAMETRIZATION: 2D Airfoil geometries are currently parametrized as NACA 4 digit airfoils with three parameters;

• m: Maximum camber of the airfoil divided by its chord
• p: Maximum camber location of the airfoil along its chord
• t: Maximum thickness of the airfoil divided by its chord

AERODYNAMIC ANALYSIS: Aerodynamic characteristics of the airfoil is currently solved by XFOIL tool, the outputs are;

• Aerodynamic coefficients, CL, CDP, CD, CM
• Pressure distribution of the upper and lower surfaces
• Airfoil curve in x-y coordinates

OPTIMIZATION ALGORITHM: Optimization is based on maximizing CL/CD value. The genetic algorithm used contains;

• Crossover and mutation rates that can be rearranged
• Tournament selection method to define new generations
• Fitness history and best individual log

DISPLAY FORMAT: Analysis and optimization processes are visualized for better ease of operation including;

• Displaying airfoil curve upper and lower surfaces seperated

• Pressure distribution over its surfaces with transiiton points

• Real time fitness history and best individuals of each generation

  Fitness history example #1:

  Fitness history example #2:

TO BE ADDED:

• Using CST parametrization instead of NACA 4 digit airfoils
• Better handling of XFOIL and its outputs to increase performance
• Improvised genetic algorithm with adaptive mutation and elitism factor
• Graphic used interface to maintain the optimization proccess better