NREL's S811 Airfoil (s811-nr)
NREL's S811 Airfoil - NREL HAWT airfoil S811 root
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(s811-nr) NREL's S811 Airfoil NREL HAWT airfoil S811 root Max thickness 26.3% at 27.4% chord. Max camber 1.7% at 76.4% chord Source NWTC National WInd Technology Center Source dat file The dat file is in Selig format |
NREL's S811 Airfoil x/c y/c 1.00000 0.00000 0.99619 0.00074 0.98519 0.00323 0.96793 0.00761 0.94535 0.01352 0.91804 0.02028 0.88610 0.02727 0.84950 0.03440 0.80858 0.04188 0.76398 0.04975 0.71636 0.05796 0.66646 0.06641 0.61500 0.07493 0.56276 0.08335 0.51049 0.09140 0.45894 0.09881 0.40887 0.10523 0.36098 0.11025 0.31597 0.11314 0.27382 0.11289 0.23368 0.10934 0.19534 0.10331 0.15926 0.09538 0.12588 0.08587 0.09559 0.07507 0.06876 0.06328 0.04575 0.05078 0.02689 0.03785 0.01252 0.02483 0.00312 0.01213 0.00000 0.00000 0.00000 -0.00017 0.00330 -0.01344 0.01158 -0.02841 0.02410 -0.04435 0.04047 -0.06074 0.06034 -0.07716 0.08330 -0.09318 0.10892 -0.10833 0.13681 -0.12211 0.16655 -0.13392 0.19784 -0.14311 0.23045 -0.14893 0.26460 -0.15049 0.30087 -0.14743 0.33981 -0.13961 0.38235 -0.12742 0.42897 -0.11218 0.47922 -0.09522 0.53243 -0.07757 0.58775 -0.06021 0.64413 -0.04401 0.70040 -0.02967 0.75525 -0.01772 0.80734 -0.00847 0.85534 -0.00200 0.89799 0.00184 0.93420 0.00341 0.96306 0.00321 0.98380 0.00192 0.99602 0.00056 1.00000 0.00000 |
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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 S811 Airfoil (s811-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s811-nr | 50,000 | 9 | 6.1 at α=-0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s811-nr | 50,000 | 5 | 7.5 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s811-nr | 100,000 | 9 | 12.8 at α=15° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s811-nr | 100,000 | 5 | 28.4 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s811-nr | 200,000 | 9 | 48.8 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s811-nr | 200,000 | 5 | 52.3 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s811-nr | 500,000 | 9 | 79.1 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s811-nr | 500,000 | 5 | 76 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s811-nr | 1,000,000 | 9 | 99.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s811-nr | 1,000,000 | 5 | 90.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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