NREL's S816 Airfoil (s816-nr)
NREL's S816 Airfoil - NREL HAWT airfoil S816 primary 21.0% Dia=30 to 50 m Re=4.0E+6 Clmax(S)=1.20 Clmax(R)=1.17 Restrained max lift coef
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(s816-nr) NREL's S816 Airfoil NREL HAWT airfoil S816 primary 21.0% Dia=30 to 50 m Re=4.0E+6 Clmax(S)=1.20 Clmax(R)=1.17 Restrained max lift coef Max thickness 21% at 39% chord. Max camber 1.8% at 67.6% chord Source NWTC National WInd Technology Center Source dat file The dat file is in Selig format |
NREL's S816 Airfoil x/c y/c 1.000000 0.000000 0.996139 0.000651 0.985006 0.003106 0.967648 0.007693 0.945108 0.014107 0.918057 0.021688 0.886684 0.029800 0.850938 0.038386 0.811363 0.047651 0.768687 0.057519 0.723658 0.067795 0.677026 0.078194 0.629529 0.088357 0.581877 0.097848 0.534734 0.106146 0.488712 0.112580 0.444024 0.115865 0.399264 0.115944 0.354691 0.113814 0.310843 0.109842 0.268201 0.104282 0.227257 0.097354 0.188452 0.089266 0.152242 0.080231 0.119020 0.070459 0.089205 0.060180 0.063139 0.049617 0.041222 0.039012 0.023779 0.028504 0.010945 0.018311 0.003011 0.008777 0.000227 0.002063 0.000010 0.000379 0.000002 0.000169 0.000178 -0.001513 0.000945 -0.003074 0.002207 -0.004692 0.003672 -0.006156 0.014071 -0.012887 0.030485 -0.019801 0.052544 -0.026861 0.080161 -0.034320 0.112634 -0.042883 0.148454 -0.052315 0.187053 -0.062182 0.227531 -0.072135 0.269005 -0.082228 0.309260 -0.090933 0.348681 -0.095266 0.389942 -0.094987 0.433138 -0.091132 0.478623 -0.084226 0.526146 -0.075203 0.575246 -0.064753 0.625372 -0.053529 0.675866 -0.042173 0.725961 -0.031295 0.774778 -0.021447 0.821346 -0.013082 0.864623 -0.006523 0.903547 -0.001926 0.937074 0.000740 0.964248 0.001689 0.984158 0.001296 0.996076 0.000427 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 S816 Airfoil (s816-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s816-nr | 50,000 | 9 | 16.9 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s816-nr | 50,000 | 5 | 12.9 at α=12.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s816-nr | 100,000 | 9 | 21 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s816-nr | 100,000 | 5 | 22.2 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s816-nr | 200,000 | 9 | 59 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s816-nr | 200,000 | 5 | 60.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s816-nr | 500,000 | 9 | 96.9 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s816-nr | 500,000 | 5 | 91 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s816-nr | 1,000,000 | 9 | 121.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s816-nr | 1,000,000 | 5 | 108.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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