Airfoil Data
NACA671215

The NACA 67,1-215 is a 8.6% chord-thickness airfoil with a maximum camber of 4.3% at 50% chord, suited to transonic and supercritical wing sections where aft-camber reduces wave drag. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -4.3°.

Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 59 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The slim profile minimises pressure drag at higher speeds but leaves limited spar depth for structural integration.

Designers evaluating the NACA671215 typically compare it against profiles of similar thickness: NACA 63(2)-215 MOD B, E193 (10.22%), PSU-90-125WL, NACA 66(2)-215, EPPLER 635 AIRFOIL. The NACA M20 AIRFOIL is another reference profile frequently considered alongside it.