Airfoil Data
MRC16-85
MRC16-85
Wing Geometry Simulator
The MRC16-85 is a 9.0% chord-thickness airfoil with a maximum camber of 4.5% 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 -4.5°.
Thin airfoil theory predicts a stall angle near 11.7° and a peak lift-to-drag ratio around 61 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 MRC16-85 typically compare it against profiles of similar thickness: GOE 547 AIRFOIL, S4320, AS5046 (16%) | Ref: http://www.krnet.org/as504x/ [original link: http://amber.aae.uiuc.edu/~ashok/kr2/airfoils/tests/], NASA SC(2)-0518 AIRFOIL, SD7034. The HOBIE is another reference profile frequently considered alongside it.
Design wings in your spreadsheet
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Related Airfoils
Engineers evaluating the MRC16-85 frequently compare it against profiles with comparable geometric constraints. Below are the closest matches based on maximum thickness (9.0%) and max camber (4.5%).
GOETTINGEN-547
GOE 547 AIRFOIL
SELIG-S4320
S4320
SELIG-AS5046
AS5046 (16%) | Ref: http://www.krnet.org/as504x/ [original link: http://amber.aae.uiuc.edu/~ashok/kr2/airfoils/tests/]
NASA-SC20518
NASA SC(2)-0518 AIRFOIL
SELIG-SD7034
SD7034
GOETTINGEN-547
GOE 547 AIRFOIL
SELIG-S4320
S4320
SELIG-AS5046
AS5046 (16%) | Ref: http://www.krnet.org/as504x/ [original link: http://amber.aae.uiuc.edu/~ashok/kr2/airfoils/tests/]
NASA-SC20518
NASA SC(2)-0518 AIRFOIL
SELIG-SD7034
SD7034
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