Airfoil Data
AH21-7
AH21 7% version (Andrew Hollom)
Wing Geometry Simulator
The AH21 7% version (Andrew Hollom) is a thin 6.6% chord-thickness airfoil with a maximum camber of 3.3% 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 -3.3°.
Thin airfoil theory predicts a stall angle near 11.9° and a peak lift-to-drag ratio around 54 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 AH21-7 typically compare it against profiles of similar thickness: NPL 9660 AIRFOIL, NPL 9615 AIRFOIL, EPPLER 818 HYDROFOIL AIRFOIL, GOE 563 AIRFOIL, RG 14 10% AIRFOIL. The HQ 0/7 AIRFOIL is another reference profile frequently considered alongside it.
Design wings in your spreadsheet
AeroSheet loads AH21-7 airfoils directly into Google Sheets. Polars, 3D splines, Fusion 360 export, without leaving your spreadsheet.
Related Airfoils
Engineers evaluating the AH21-7 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (6.6%) and max camber (3.3%).
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