Airfoil Data
MRC-20
MRC-20
Wing Geometry Simulator
The MRC-20 is a 10.7% chord-thickness airfoil with a maximum camber of 5.4% at 38% chord, suited to general-aviation and UAV wing design. At zero angle of attack the cambered geometry generates positive lift, giving an estimated zero-lift angle of -5.4°.
Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 65 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 11% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
Designers evaluating the MRC-20 typically compare it against profiles of similar thickness: USA 40 AIRFOIL, WORTMANN FX 05-H-126 AIRFOIL, GOE 360 AIRFOIL, GOE 633 AIRFOIL, GOE 509 AIRFOIL. The FX S 03-182 AIRFOIL is another reference profile frequently considered alongside it.
Design wings in your spreadsheet
AeroSheet loads MRC-20 airfoils directly into Google Sheets. Polars, 3D splines, Fusion 360 export, without leaving your spreadsheet.
Related Airfoils
Engineers evaluating the MRC-20 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (10.7%) and max camber (5.4%).
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