NREL's S801 Airfoil (s801-nr)
NREL's S801 Airfoil - NREL HAWT airfoil S801 primary 13.5% Not recommended
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(s801-nr) NREL's S801 Airfoil NREL HAWT airfoil S801 primary 13.5% Not recommended Max thickness 13.5% at 37.8% chord. Max camber 3.7% at 47.1% chord Source NWTC National WInd Technology Center Source dat file The dat file is in Selig format |
NREL's S801 Airfoil x/c y/c 1.00000 0.00000 0.99656 0.00112 0.98696 0.00457 0.97239 0.00989 0.95321 0.01609 0.92915 0.02276 0.90032 0.03008 0.86722 0.03808 0.83039 0.04663 0.79041 0.05559 0.74789 0.06472 0.70344 0.07377 0.65769 0.08239 0.61124 0.09021 0.56467 0.09667 0.51809 0.10109 0.47124 0.10334 0.42425 0.10384 0.37763 0.10284 0.33190 0.10044 0.28753 0.09676 0.24498 0.09191 0.20471 0.08598 0.16712 0.07910 0.13262 0.07139 0.10155 0.06298 0.07425 0.05402 0.05098 0.04463 0.03196 0.03498 0.01735 0.02523 0.00723 0.01556 0.00150 0.00628 0.00000 0.00000 0.00018 -0.00196 0.00430 -0.00847 0.01441 -0.01382 0.03006 -0.01864 0.05097 -0.02281 0.07688 -0.02628 0.10754 -0.02903 0.14262 -0.03110 0.18173 -0.03249 0.22445 -0.03327 0.27028 -0.03346 0.31867 -0.03311 0.36905 -0.03224 0.42079 -0.03088 0.47326 -0.02899 0.52580 -0.02655 0.57775 -0.02341 0.62855 -0.01915 0.67839 -0.01332 0.72786 -0.00655 0.77663 -0.00020 0.82356 0.00477 0.86743 0.00781 0.90682 0.00861 0.94021 0.00742 0.96650 0.00509 0.98521 0.00259 0.99632 0.00070 1.00000 0.00000 |
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Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
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Polars for NREL's S801 Airfoil (s801-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s801-nr | 50,000 | 9 | 31.7 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s801-nr | 50,000 | 5 | 27.1 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s801-nr | 100,000 | 9 | 52.1 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s801-nr | 100,000 | 5 | 52.2 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s801-nr | 200,000 | 9 | 85.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s801-nr | 200,000 | 5 | 80.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s801-nr | 500,000 | 9 | 118.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s801-nr | 500,000 | 5 | 112 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s801-nr | 1,000,000 | 9 | 147.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s801-nr | 1,000,000 | 5 | 133.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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