This is Xoptfoil, an airfoil optimization code using the Xfoil aerodynamics
engine.
Copyright 2017-2019 Daniel Prosser.
Xoptfoil uses the GNU Public License Version 3, a copy of which can be found in the license directory.
Code features:
-- Supports up to 30 operating points during optimization and multiple user-defined constraints
-- Each operating point has a specified lift coefficient or angle of attack, Reynolds number, Mach number, and flap deflection
-- Different optimization objectives (minimize drag, maximize glide slope, minimize sink rate, maximize lift, or move the turbulent transition point aft) can be set at each operating point
-- Each operating point is assigned a relative weight (importance) by the user
-- Available constraints include thickness, camber, curvature, pitching moment, flap angles, and trailing edge wedge angle
-- Currently included optimization algorithms: particle swarm, genetic algorithm, and Nelder-Mead simplex algorithm
-- The optimizer is robust: many checks for reasonable geometry and Xfoil convergence in place
-- Particle swarm and genetic algorithm run in parallel (must be compiled manually; pre-compiled binaries are serial)
-- Xfoil engine accurately predicts transition, separation bubbles, and stall at low Reynolds numbers
-- Includes a graphical tool to monitor the optimization and plot the results
Installing and compiling instructions are included in the User Guide.
Options are stored in the fortran namelist file inputs.txt. This file sets basic optimization options, operating conditions, constraints, and Xfoil paneling and run settings.
For complete version notes, see ChangeLog.
