Airfoil Data
AH95160
AH 95-160
Wing Geometry Simulator
The AH 95-160 is a 13.5% chord-thickness airfoil with a maximum camber of 6.7% at 41% 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 -6.7°.
Thin airfoil theory predicts a stall angle near 11.1° and a peak lift-to-drag ratio around 71 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 13% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
Designers evaluating the AH95160 typically compare it against profiles of similar thickness: GOE 628 AIRFOIL, FX 76-MP-120, FX S 02-196 AIRFOIL, NACA 65(4)-421 a=0.5, FX 73-CL1-152. The LNV109A is another reference profile frequently considered alongside it.
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Engineers evaluating the AH95160 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (13.5%) and max camber (6.7%).
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