Airfoil Optimization

A Hess-Smith panel-method airfoil optimizer with a live portfolio demo.

Project code
  • Python
  • NumPy
  • Hess-Smith panel method
  • Nelder-Mead
  • Next.js

Gallery

Interactive Demo

This demo runs the same in-repo optimizer used by the project files. The browser streams candidate airfoils while the Python backend evaluates NACA 4-digit geometry with the Hess-Smith solver, applies the semi-empirical drag model, and reports the best feasible design found for the lift constraint.

Airfoil Optimizer

Idle
Advanced settings

Live Geometry

Waiting for run
x/cy/c
CurrentBest foundNACA 0012NACA 2412NACA 4412

Summary

No result
Maximum camber-
Camber location-
Maximum thickness-
Lift coefficient-
Modeled drag coefficient-
Lift-to-drag ratio-

No optimization run yet.

Implementation Notes

  • The optimizer searches over maximum camber, camber location, and maximum thickness.
  • Hess-Smith supplies lift, pressure coefficient, and moment diagnostics; the objective uses the modeled drag coefficient described in the project design notes.
  • The final result is reported as the best found design from a multi-start Nelder-Mead search, not as a guaranteed global optimum.