Airfoil Data
AH21-9
AH21 9% version (Andrew Hollom)
Wing Geometry Simulator
The AH21 9% version (Andrew Hollom) is a thin 5.1% chord-thickness airfoil with a maximum camber of 2.6% 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 -2.6°.
Thin airfoil theory predicts a stall angle near 11.9° and a peak lift-to-drag ratio around 50 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.
Designers evaluating the AH21-9 typically compare it against profiles of similar thickness: JX-GS-10, AG03 (flat aft bottom), AG46c -03f, Supermarine 371-II (tip), AG16. The PROPFAN CRUISE MISSILE WING AIRFOIL is another reference profile frequently considered alongside it.
Design wings in your spreadsheet
AeroSheet loads AH21-9 airfoils directly into Google Sheets. Polars, 3D splines, Fusion 360 export, without leaving your spreadsheet.
Related Airfoils
Engineers evaluating the AH21-9 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (5.1%) and max camber (2.6%).
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