Airfoil Data
AH93K132

The AH 93-K-132/15 is a 10.1% chord-thickness airfoil with a maximum camber of 5.1% at 41% 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 -5.1°.

Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 64 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 10% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.

Designers evaluating the AH93K132 typically compare it against profiles of similar thickness: Fage & Collins 3, AS5048 (18%) | Ref: http://www.krnet.org/as504x/ [original link: http://amber.aae.uiuc.edu/~ashok/kr2/airfoils/tests/], GOE 311 (MVA H.43) AIRFOIL, GOE 526 AIRFOIL, USA 48 AIRFOIL. The AH 93-W-215 is another reference profile frequently considered alongside it.