NREL's S815 Airfoil (s815-nr)
NREL's S815 Airfoil - NREL HAWT airfoil S815 root 26.0% Dia=20 to 30 m Re=1.2E+6 Clmax(S)=1.46 Clmax(R)=1.40 High max lift coef
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(s815-nr) NREL's S815 Airfoil NREL HAWT airfoil S815 root 26.0% Dia=20 to 30 m Re=1.2E+6 Clmax(S)=1.46 Clmax(R)=1.40 High max lift coef Max thickness 26.2% at 25.7% chord. Max camber 2.9% at 77.9% chord Source NWTC National WInd Technology Center Source dat file The dat file is in Selig format |
NREL's S815 Airfoil x/c y/c 1.000000 0.000000 0.996173 0.001133 0.985317 0.004881 0.968744 0.011230 0.947570 0.019426 0.922318 0.028413 0.892882 0.037295 0.858861 0.045992 0.820626 0.054798 0.778755 0.063696 0.733854 0.072589 0.686557 0.081333 0.637515 0.089752 0.587388 0.097641 0.536833 0.104767 0.486493 0.110878 0.436986 0.115700 0.388903 0.118923 0.342805 0.120166 0.299024 0.118640 0.256752 0.114308 0.216262 0.107924 0.178016 0.099823 0.142448 0.090268 0.109968 0.079497 0.080953 0.067752 0.055765 0.055278 0.034732 0.042339 0.018216 0.029212 0.006536 0.016218 0.001725 0.007768 0.000670 0.004717 0.000438 0.003825 0.000070 0.001733 0.000038 -0.001324 0.000429 -0.004570 0.001456 -0.009000 0.007838 -0.023840 0.018563 -0.039818 0.033214 -0.056411 0.051397 -0.073093 0.072764 -0.089487 0.096824 -0.105023 0.123271 -0.119221 0.151614 -0.131452 0.181610 -0.140977 0.213063 -0.147149 0.245908 -0.148514 0.282132 -0.145003 0.321561 -0.137586 0.364402 -0.126505 0.410645 -0.112506 0.460091 -0.096324 0.512409 -0.078791 0.567090 -0.060824 0.623409 -0.043386 0.680405 -0.027417 0.736890 -0.013751 0.791474 -0.003038 0.842638 0.004338 0.888816 0.008316 0.928515 0.009176 0.960420 0.007502 0.983194 0.004101 0.996007 0.001072 1.000000 0.000000 |
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Polars for NREL's S815 Airfoil (s815-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s815-nr | 50,000 | 9 | 3.2 at α=-1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s815-nr | 50,000 | 5 | 9 at α=15.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s815-nr | 100,000 | 9 | 26.2 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s815-nr | 100,000 | 5 | 36 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s815-nr | 200,000 | 9 | 54.4 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s815-nr | 200,000 | 5 | 54.8 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s815-nr | 500,000 | 9 | 79.5 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s815-nr | 500,000 | 5 | 75.9 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s815-nr | 1,000,000 | 9 | 99.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s815-nr | 1,000,000 | 5 | 91.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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