Airfoil Data
MRC-16
MRC-16
Wing Geometry Simulator
The MRC-16 is a 10.1% chord-thickness airfoil with a maximum camber of 5.0% at 36% 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 -5.0°.
Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 64 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The 10% thickness provides structural depth for main-spar placement without excessive drag penalty at moderate speeds.
Designers evaluating the MRC-16 typically compare it against profiles of similar thickness: GOE 550 AIRFOIL, NACA 65(3)-218, EPPLER 598 AIRFOIL, GOE 574 AIRFOIL, ARA-D 13% AIRFOIL. The FX 79-W-660A is another reference profile frequently considered alongside it.
Design wings in your spreadsheet
AeroSheet loads MRC-16 airfoils directly into Google Sheets. Polars, 3D splines, Fusion 360 export, without leaving your spreadsheet.
Related Airfoils
Engineers evaluating the MRC-16 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (10.1%) and max camber (5.0%).
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