Skip to content

Latest commit

 

History

History
20 lines (14 loc) · 1023 Bytes

README.md

File metadata and controls

20 lines (14 loc) · 1023 Bytes
Raw

Genetic-airfoil

Optimization of airfoil geometry for a high-altitude, long endurance (HALE) UAV.

Includes

  • Python-Xfoil interface to generate airfoil polar using Xfoil viscous analysis mode.
  • Conversion from PARSEC [1] parametrization to airfoil coordinates using a Chebychev grid.
  • Conversion from airfoil coordinates to PARSEC parameters through non-linear fitting via SLSQP optimization. plot
  • Optimization of airfoil geometry according to cost function f = 0.5Cl3/Cd2 + 0.3Cl/Cd + 0.2*alfa_range, where alfa_range is the range between the cruise angle of attack and the stall angle of attack. Done through a genetic algorithm formulation.

Comparison between initial parameters and optimized parameters

plot

Original vs optimized airfoil geometry

plot

References

[1] R.W. Derksen, Tim Rogalsky, “Bezier-PARSEC: An optimized aerofoil parameterization for design”, Advances in Engineering Software 41 (2010) 923-930.