NREL's S835 Airfoil (s835-nr)
NREL's S835 Airfoil - NREL HAWT airfoil S835 root 21.0% Dia=1 to 3 m Re=2.5E+5 Clmax(S)=1.20 Clmax(R)=1.03 High max lift coef
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(s835-nr) NREL's S835 Airfoil NREL HAWT airfoil S835 root 21.0% Dia=1 to 3 m Re=2.5E+5 Clmax(S)=1.20 Clmax(R)=1.03 High max lift coef Max thickness 21% at 30.5% chord. Max camber 2.4% at 78% chord Source NWTC National WInd Technology Center Source dat file The dat file is in Selig format |
NREL's S835 Airfoil x/c y/c 1.000000 0.000000 0.995932 0.000974 0.984473 0.004552 0.967194 0.010971 0.945459 0.019503 0.919943 0.029016 0.890618 0.038526 0.857149 0.047861 0.819938 0.057178 0.779531 0.066312 0.736444 0.075033 0.691173 0.083101 0.644202 0.090280 0.596002 0.096359 0.547033 0.101147 0.497745 0.104476 0.448511 0.106196 0.399664 0.106378 0.351783 0.104999 0.305188 0.102105 0.260367 0.097834 0.217816 0.092265 0.177969 0.085485 0.141266 0.077587 0.108053 0.068680 0.078706 0.058894 0.053467 0.048379 0.032658 0.037351 0.016487 0.026032 0.005368 0.014774 0.003569 0.012203 0.001995 0.009465 0.000868 0.006772 0.000259 0.003974 0.000230 0.003763 0.000015 0.000995 0.001113 -0.008866 0.006381 -0.022529 0.015773 -0.036575 0.029084 -0.050332 0.046306 -0.063467 0.067214 -0.075502 0.091816 -0.086196 0.119820 -0.095194 0.151207 -0.102304 0.185631 -0.107229 0.223218 -0.109799 0.263720 -0.110144 0.306838 -0.108293 0.352267 -0.104298 0.399699 -0.098265 0.448814 -0.090357 0.499275 -0.080810 0.550725 -0.069931 0.602768 -0.058110 0.654962 -0.045821 0.706793 -0.033614 0.757643 -0.022112 0.806764 -0.011986 0.853241 -0.003934 0.895818 0.001265 0.932596 0.003434 0.962014 0.003325 0.983186 0.002036 0.995825 0.000638 1.000000 0.000000 |
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
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Polars for NREL's S835 Airfoil (s835-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s835-nr | 50,000 | 9 | 23.7 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s835-nr | 50,000 | 5 | 19.2 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s835-nr | 100,000 | 9 | 34.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s835-nr | 100,000 | 5 | 35.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s835-nr | 200,000 | 9 | 55.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s835-nr | 200,000 | 5 | 51.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s835-nr | 500,000 | 9 | 77.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s835-nr | 500,000 | 5 | 65.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s835-nr | 1,000,000 | 9 | 88.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s835-nr | 1,000,000 | 5 | 70.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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