Airfoil Data
SC21006

The NASA SC(2)-1006 AIRFOIL is a thin 3.0% chord-thickness airfoil with a symmetrical cross-section (camber -2.2%), commonly used in aerobatic aircraft, rotorcraft blades, and tail surfaces where inverted flight symmetry is required.

Thin airfoil theory predicts a stall angle near 13.5° and a peak lift-to-drag ratio around 29 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 SC21006 typically compare it against profiles of similar thickness: NASA SC(2)-0706 AIRFOIL, NASA SC(2)-0606 AIRFOIL, NACA 16-006, EPPLER EA 8(-1)-006 AIRFOIL, NACA 0006. The NACA 0012-64 is another reference profile frequently considered alongside it.