Airfoil Data
V23010

The BOEING-VERTOL V23010-1.58 AIRFOIL is a thin 6.6% chord-thickness airfoil with a maximum camber of 3.3% at 20% chord, suited to high-speed UAVs, sailplane tip sections, and propeller blade design. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -3.3°.

Thin airfoil theory predicts a stall angle near 11.9° and a peak lift-to-drag ratio around 54 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 V23010 typically compare it against profiles of similar thickness: BOEING 707 .40 SPAN AIRFOIL, MH 61 10.26%, LOCKHEED C-5A BL0 AIRFOIL, BELL/WORTMANN FX 69-H-083 AIRFOIL, GOE 411 AIRFOIL. The GOE 395 AIRFOIL is another reference profile frequently considered alongside it.