Airfoil Data
NACA747A315

The NACA 747A315 is a 10.0% chord-thickness airfoil with a maximum camber of 5.0% at 35% 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 -5.0°.

Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 63 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.

The NACA747A315 appears in the wing design of at least 4 documented aircraft, including designs from DRS and Jameson. Its proven track record across conventional and rotorcraft designs makes it one of the more field-validated profiles in the UIUC database.

Designers evaluating the NACA747A315 typically compare it against profiles of similar thickness: AS6098 | Ananda-Selig | AIAA Paper 2018-0310, EPPLER 540 AIRFOIL, S2027, NASA/LANGLEY MS(1)-0317 AIRFOIL, Prandtl-D Centerline NASA TP-2016-219072. The NACA M21 AIRFOIL is another reference profile frequently considered alongside it.