NREL's S817 Airfoil (s817-nr)
NREL's S817 Airfoil - NREL HAWT airfoil S817 tip 16.0% Dia=30 to 50 m Re=3.0E+6 Clmax(S)=1.10 Clmax(R)=1.08 Restrained max lift coef
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(s817-nr) NREL's S817 Airfoil NREL HAWT airfoil S817 tip 16.0% Dia=30 to 50 m Re=3.0E+6 Clmax(S)=1.10 Clmax(R)=1.08 Restrained max lift coef Max thickness 16% at 51.1% chord. Max camber 2.8% at 41.1% chord Source NWTC National WInd Technology Center Source dat file The dat file is in Selig format |
NREL's S817 Airfoil x/c y/c 1.000000 0.000000 0.996181 0.000538 0.985115 0.002693 0.967742 0.006897 0.945064 0.013016 0.917813 0.020567 0.886342 0.029037 0.850827 0.038354 0.811952 0.048605 0.770556 0.059582 0.727479 0.070903 0.683540 0.082026 0.639510 0.092179 0.595770 0.099994 0.551323 0.104955 0.506064 0.107442 0.460088 0.107831 0.413876 0.106495 0.367930 0.103634 0.322764 0.099414 0.278854 0.093990 0.236695 0.087518 0.196730 0.080162 0.159422 0.072091 0.125168 0.063482 0.094395 0.054524 0.067447 0.045401 0.044732 0.036303 0.026561 0.027298 0.013037 0.018535 0.004428 0.010189 0.000360 0.002472 0.000097 0.001209 0.000009 -0.000344 0.000088 -0.001044 0.000269 -0.001673 0.000601 -0.002252 0.001068 -0.002831 0.001348 -0.003124 0.002331 -0.003985 0.009208 -0.007511 0.023293 -0.011505 0.043224 -0.015059 0.069056 -0.018360 0.100341 -0.021950 0.136148 -0.025898 0.175927 -0.030099 0.218923 -0.034424 0.264584 -0.038702 0.312212 -0.042753 0.361251 -0.046380 0.411034 -0.049379 0.461007 -0.051521 0.510533 -0.052546 0.559060 -0.052087 0.606201 -0.049264 0.652988 -0.043963 0.699386 -0.036994 0.745363 -0.029123 0.790264 -0.021329 0.833208 -0.014263 0.873235 -0.008386 0.909350 -0.003976 0.940561 -0.001118 0.965947 0.000302 0.984691 0.000585 0.996152 0.000262 1.000000 0.000000 |
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Similar airfoils
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Polars for NREL's S817 Airfoil (s817-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s817-nr | 50,000 | 9 | 21.5 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s817-nr | 50,000 | 5 | 17.9 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s817-nr | 100,000 | 9 | 25.9 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s817-nr | 100,000 | 5 | 26.6 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s817-nr | 200,000 | 9 | 45.3 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s817-nr | 200,000 | 5 | 53 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s817-nr | 500,000 | 9 | 105.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s817-nr | 500,000 | 5 | 101.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s817-nr | 1,000,000 | 9 | 137.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s817-nr | 1,000,000 | 5 | 126 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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