Airfoil Data
NACA0024
NACA 0024
Wing Geometry Simulator
The NACA 0024 is a 12.0% chord-thickness airfoil with a maximum camber of 6.0% 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 -6.0°.
Thin airfoil theory predicts a stall angle near 11.6° and a peak lift-to-drag ratio around 69 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 12% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
The NACA0024 appears in the wing design of at least 1 documented aircraft — notably by Bell. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.
Designers evaluating the NACA0024 typically compare it against profiles of similar thickness: Bambino 6, GOE 703 AIRFOIL, RAF 6 AIRFOIL, 12%, LE rad. 0.012, TE rad. 0.0092, NACA TR259 smoothed, DAE-31 AIRFOIL, EPPLER 1214 AIRFOIL. The LOCKHEED L-188 ROOT AIRFOIL is another reference profile frequently considered alongside it.
Aircraft Using the NACA0024 Airfoil
Bell 209 AH-1 | Bell | NACA 0030 | NACA 0024 |
Wing lofting: 1 of these aircraft taper from NACA0024 at the root to a different tip section. Use the Tapered filter to isolate them, then click any tip airfoil link to compare geometries.
Related Airfoils
Engineers evaluating the NACA0024 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (12.0%) and max camber (6.0%).