Spectrum — NACA 4-Digit Airfoil Generator

Airfoil Definition

NACA code (4 digits)

Digit 1: max camber (%c) · Digit 2: camber position (×10 %c) · Digits 3–4: max thickness (%c)

Max camber (m)%c

Camber position (p)%c

Max thickness (t)%c

Chord length (final)

Unit

Trailing edge is always closed. Chord length is the exact final part length, even after a 3D-printing cut.

3D Printing (FDM)

Cut trailing edge for printability, keep chord length fixed Minimum trailing edge thickness

0.2 mm 0.4 mm

Point Distribution

Total points (upper + lower)

239 total (120 per surface)

Show original high-resolution profile for comparison

Airfoil surface Mean camber line Chord line High-res reference Scroll to zoom · Drag to pan

Summary

Comparison Overlay

No airfoils added yet — use "Add to comparison overlay" to stack shapes.

Export

The .dat file uses the classic two-column normalized format (title line + x/c, y/c), normalized by the true achieved chord so the trailing edge lands at exactly x/c = 1.0000 — compatible with Fusion 360 import scripts, XFOIL, and most airfoil readers. The .csv holds full-scale X, Y coordinates in your chosen unit.

Reynolds number

Angle of attack (°)

Pressure loading (Δcp) along chord

Lift coefficient vs. angle of attack

Drag coefficient vs. angle of attack

Panel-method estimate for preliminary design — not a substitute for XFOIL or CFD.

Ordered trailing edge → upper surface → leading edge → lower surface → trailing edge.

#	x/c	y/c