Airfoil Data
MI-STRUT1

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.