Airfoil Data
NACA23024

The NACA 23024 is a 13.5% chord-thickness airfoil with a maximum camber of 6.8% at 30% chord, suited to high-lift UAV wings, RC sailplanes, and low-Reynolds-number slow-flyers. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -6.8°.

Thin airfoil theory predicts a stall angle near 11.1° and a peak lift-to-drag ratio around 71 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 14% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

The NACA23024 appears in the wing design of at least 9 documented aircraft, including designs from Miles and Turbay. 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 NACA23024 typically compare it against profiles of similar thickness: EPPLER 748 AIRFOIL, St. CYR 24 (Bartel 35-IIIC), GOE 8K AIRFOIL, GOE 573 AIRFOIL, GOE 423 AIRFOIL. The NACA 23012 12% is another reference profile frequently considered alongside it.