Airfoil Data
NACA633018

The NACA 63(3)-018 is a 9.0% chord-thickness airfoil with a maximum camber of 4.5% at 34% chord, suited to general-aviation and UAV wing design. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -4.5°.

Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 61 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 NACA633018 typically compare it against profiles of similar thickness: EPPLER 327 AIRFOIL, E195 (11.82%), SD7034, NACA 0018, AS5046 (16%) | Ref: http://www.krnet.org/as504x/ [original link: http://amber.aae.uiuc.edu/~ashok/kr2/airfoils/tests/]. The NACA 65(1)-212 is another reference profile frequently considered alongside it.