NREL's S812 Airfoil (s812-nr)
NREL's S812 Airfoil - NREL HAWT airfoil S812 primary
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(s812-nr) NREL's S812 Airfoil NREL HAWT airfoil S812 primary Max thickness 21% at 39.6% chord. Max camber 1.6% at 77% chord Source NWTC National WInd Technology Center Source dat file The dat file is in Selig format |
NREL's S812 Airfoil x/c y/c 1.00000 0.00000 0.99622 0.00076 0.98532 0.00332 0.96832 0.00791 0.94620 0.01416 0.91957 0.02138 0.88852 0.02895 0.85300 0.03680 0.81338 0.04518 0.77037 0.05416 0.72473 0.06368 0.67730 0.07361 0.62903 0.08367 0.58100 0.09331 0.53392 0.10142 0.48768 0.10698 0.44181 0.10971 0.39609 0.10990 0.35073 0.10807 0.30627 0.10458 0.26322 0.09961 0.22208 0.09333 0.18329 0.08590 0.14728 0.07750 0.11447 0.06829 0.08520 0.05845 0.05982 0.04818 0.03861 0.03768 0.02182 0.02718 0.00969 0.01696 0.00239 0.00728 0.00000 0.00000 0.00007 -0.00115 0.00429 -0.00826 0.01562 -0.01526 0.03299 -0.02269 0.05617 -0.03080 0.08431 -0.04006 0.11621 -0.05032 0.15100 -0.06102 0.18802 -0.07160 0.22664 -0.08149 0.26633 -0.08997 0.30686 -0.09628 0.34820 -0.09988 0.39050 -0.10030 0.43411 -0.09760 0.47877 -0.09211 0.52437 -0.08354 0.57163 -0.07217 0.62070 -0.05937 0.67084 -0.04632 0.72113 -0.03387 0.77054 -0.02272 0.81792 -0.01341 0.86208 -0.00625 0.90185 -0.00137 0.93610 0.00133 0.96383 0.00212 0.98403 0.00150 0.99606 0.00046 1.00000 0.00000 |
Dat file parser warnings
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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 S812 Airfoil (s812-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s812-nr | 50,000 | 9 | 17.4 at α=13.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s812-nr | 50,000 | 5 | 14.2 at α=11.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s812-nr | 100,000 | 9 | 23.9 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s812-nr | 100,000 | 5 | 25.8 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s812-nr | 200,000 | 9 | 56.2 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s812-nr | 200,000 | 5 | 59.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s812-nr | 500,000 | 9 | 92.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s812-nr | 500,000 | 5 | 87.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s812-nr | 1,000,000 | 9 | 116.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s812-nr | 1,000,000 | 5 | 105.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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