Airfoil Data
IST-MT1-24
IST-MT1-24
Wing Geometry Simulator
The IST-MT1-24 is a 15.0% chord-thickness airfoil with a maximum camber of 7.5% at 34% 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 -7.5°.
Thin airfoil theory predicts a stall angle near 10.6° and a peak lift-to-drag ratio around 73 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 15% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
Designers evaluating the IST-MT1-24 typically compare it against profiles of similar thickness: GOE 652 AIRFOIL, FX 73-CL3-152, GOE 383 AIRFOIL, GOE 217 (MVA MK.12) AIRFOIL, IST-MT1-15. The OAF117 AIRFOIL is another reference profile frequently considered alongside it.
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Related Airfoils
Engineers evaluating the IST-MT1-24 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (15.0%) and max camber (7.5%).
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