Airfoil Data
SG6042

The SG6042 is a 8.6% chord-thickness airfoil with a maximum camber of 4.3% at 41% 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 -4.3°.

Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 60 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 SG6042 typically compare it against profiles of similar thickness: GOE 178 AIRFOIL, EPPLER 379 AIRFOIL, MARSKE PIONEER IID ROOT AIRFOIL (NACA 431012A/24112 HYBRID), E231, GOE 177 AIRFOIL. The NACA 0010 is another reference profile frequently considered alongside it.