Airfoil Data
MI-STRUT1
MI-STRUT1
Wing Geometry Simulator
The MI-STRUT1 is a thick 16.5% chord-thickness airfoil with a maximum camber of 8.2% at 30% 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 -8.2°.
Thin airfoil theory predicts a stall angle near 10.0° and a peak lift-to-drag ratio around 74 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 16% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
Designers evaluating the MI-STRUT1 typically compare it against profiles of similar thickness: GOE 384 AIRFOIL, GOE 482 AIRFOIL, GOE 243 (MVA PR.3) AIRFOIL, St. CYR 234 (Bartel 17-IC), USA 34 AIRFOIL. The GOE 596 AIRFOIL is another reference profile frequently considered alongside it.
Design wings in your spreadsheet
AeroSheet loads MI-STRUT1 airfoils directly into Google Sheets. Polars, 3D splines, Fusion 360 export, without leaving your spreadsheet.
Related Airfoils
Engineers evaluating the MI-STRUT1 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (16.5%) and max camber (8.2%).
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