Airfoil Data
SUPERMARINE371I

The Supermarine 371-I (root) is a thin 7.4% chord-thickness airfoil with a maximum camber of 3.7% at 40% 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 -3.7°.

Thin airfoil theory predicts a stall angle near 11.8° and a peak lift-to-drag ratio around 56 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 SUPERMARINE371I appears in the wing design of at least 5 documented aircraft — notably by Supermarine. Its proven track record across canard designs makes it one of the more field-validated profiles in the UIUC database.

Designers evaluating the SUPERMARINE371I typically compare it against profiles of similar thickness: GOE 101 AIRFOIL, OAF117 AIRFOIL, HQ 1.5/12 AIRFOIL, SA7025, S8038 (13%). The SC(2)-0714 | Supercritical airfoil (coordinates from Raymer w/ one correction). These coordinates are actual model coordinates, not coordinates as designed. Ref: NASA TP-2890 is another reference profile frequently considered alongside it.