Airfoil Data
AH82150A

The AH 82-150 A is a 10.8% chord-thickness airfoil with a maximum camber of 5.4% at 40% 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 -5.4°.

Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 66 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 11% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

Designers evaluating the AH82150A typically compare it against profiles of similar thickness: BOEING VERTOL V43015-2.48 AIRFOIL, FX 75-VG-166/22, GOE 478 AIRFOIL, GOE 190 (MVA MK.18) AIRFOIL, MH 115 11.06%. The S4233-136-84 is another reference profile frequently considered alongside it.