Airfoil Data
NACA23015

The NACA 23015 is a 9.1% chord-thickness airfoil with a maximum camber of 4.5% at 25% 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.

The NACA23015 appears in the wing design of at least 263 documented aircraft, including designs from Grumman and Cessna. 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 NACA23015 typically compare it against profiles of similar thickness: Gottingen 765 airfoil (recovered). Thick: .144 LE radius: 0.02062 LE slope: 0.17300, GOE 402 AIRFOIL, GOE 385 AIRFOIL, NACA 66,2-(1.8)15.5 A=.6 P-51 ROOT AIRFOIL, GOE 308 (MVA H.40) AIRFOIL. The NACA 23012 12% is another reference profile frequently considered alongside it.