Airfoil Data
P51DTIP

The P-51D TIP (BL215) AIRFOIL is a thin 7.0% chord-thickness airfoil with a maximum camber of 3.5% at 46% 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 -3.5°.

Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 55 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 P51DTIP typically compare it against profiles of similar thickness: NASA SC(2)-0614 AIRFOIL, EH 2.0/10, MH 26 10.99%, NACA M13 AIRFOIL, S8035 for RC aerobatic 14% thick. The NACA 642-015A AIRFOIL is another reference profile frequently considered alongside it.