Airfoil Data
MRC16-95
MRC16-95
Wing Geometry Simulator
The MRC16-95 is a 9.7% chord-thickness airfoil with a maximum camber of 4.9% 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 -4.9°.
Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 63 at typical UAV and light-aircraft Reynolds numbers — useful benchmarks before running a full XFOIL or NeuralFoil polar. The slim profile minimises pressure drag at higher speeds but leaves limited spar depth for structural integration.
Designers evaluating the MRC16-95 typically compare it against profiles of similar thickness: GOE 358 AIRFOIL, GOE 359 AIRFOIL, EPPLER 555 AIRFOIL, FX 38-153 AIRFOIL, EPPLER 337 AIRFOIL. The USA 35 A AIRFOIL is another reference profile frequently considered alongside it.
Design wings in your spreadsheet
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Related Airfoils
Engineers evaluating the MRC16-95 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (9.7%) and max camber (4.9%).
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