AeroForge workspace

Airfoil polar

XFOIL polar over an alpha sweep. CL, CD, Cm, L/D. Analytical fallback if XFOIL absent.

Project
Units
IdleAbout
How to use this tool
  1. 1Pick a section (.dat) and choose your α range.
  2. 2Hit Run — defaults give you a sane sea-level polar.
  3. 3Open Advanced parameters if you need Re, Mach, panel/iteration overrides.
New here? Hit defaults and press Run to see a typical NACA 0012 polar.

Geometry

α range

°
°
°
°
Advanced parameters
m/s
m (ISA)
m
—
—
iters

Most users never need these. Defaults give a sane sea-level XFOIL run with auto-derived Re and Mach.

Results

Run the solver to see CLLift coefficient — non-dimensional lift force., CDDrag coefficient — non-dimensional drag force., CmPitching moment coefficient about the quarter-chord. and the polar curve.

Tip: a sweep from -5° to 15° at 1° resolution is a good first look.