Airfoil Data
USA35A

The USA 35 A AIRFOIL is a thick 15.3% chord-thickness airfoil with a maximum camber of 7.7% at 29% 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 -7.7°.

Thin airfoil theory predicts a stall angle near 10.4° and a peak lift-to-drag ratio around 73 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 15% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

The USA35A appears in the wing design of at least 4 documented aircraft, including designs from Dunn and Fernic. 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 USA35A typically compare it against profiles of similar thickness: USA 35 AIRFOIL, GOE 386 AIRFOIL, GOE 228 (MVA H.38) AIRFOIL, Griffith 30% Suction Airfoil, GOE 222 (MVA H.33) AIRFOIL. The HT 14 is another reference profile frequently considered alongside it.