NREL's S809 Airfoil (s809-nr)
NREL's S809 Airfoil - NREL HAWT airfoil S809 primary 21.0% Re=2.0E+6 Clmax(S)=1.00 Restrained max lift coef
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(s809-nr) NREL's S809 Airfoil NREL HAWT airfoil S809 primary 21.0% Re=2.0E+6 Clmax(S)=1.00 Restrained max lift coef Max thickness 21% at 39.5% chord. Max camber 1% at 82.3% chord Source NWTC National WInd Technology Center Source dat file The dat file is in Selig format |
NREL's S809 Airfoil x/c y/c 1.000000 0.000000 0.996203 0.000487 0.985190 0.002373 0.967844 0.005960 0.945073 0.011024 0.917488 0.017033 0.885293 0.023458 0.848455 0.030280 0.807470 0.037766 0.763042 0.045974 0.715952 0.054872 0.667064 0.064353 0.617331 0.074214 0.567830 0.084095 0.519832 0.093268 0.474243 0.099392 0.428461 0.101760 0.382612 0.101840 0.337260 0.100070 0.292970 0.096703 0.250247 0.091908 0.209576 0.085851 0.171409 0.078687 0.136174 0.070580 0.104263 0.061697 0.076035 0.052224 0.051823 0.042352 0.031910 0.032299 0.016590 0.022290 0.006026 0.012615 0.000658 0.003723 0.000204 0.001942 0.000000 -0.000020 0.000213 -0.001794 0.001045 -0.003477 0.001208 -0.003724 0.002398 -0.005266 0.009313 -0.011499 0.023230 -0.020399 0.042320 -0.030269 0.065877 -0.040821 0.093426 -0.051923 0.124111 -0.063082 0.157653 -0.073730 0.193738 -0.083567 0.231914 -0.092442 0.271438 -0.099905 0.311968 -0.105281 0.353370 -0.108181 0.395329 -0.108011 0.438273 -0.104552 0.481920 -0.097347 0.527928 -0.086571 0.576211 -0.073979 0.626092 -0.060644 0.676744 -0.047441 0.727211 -0.035100 0.776432 -0.024204 0.823285 -0.015163 0.866630 -0.008204 0.905365 -0.003363 0.938474 -0.000487 0.965086 0.000743 0.984478 0.000775 0.996141 0.000290 1.000000 0.000000 |
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 S809 Airfoil (s809-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s809-nr | 50,000 | 9 | 15.5 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s809-nr | 50,000 | 5 | 13.9 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s809-nr | 100,000 | 9 | 23.4 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s809-nr | 100,000 | 5 | 26.8 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s809-nr | 200,000 | 9 | 51.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s809-nr | 200,000 | 5 | 53.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s809-nr | 500,000 | 9 | 81.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s809-nr | 500,000 | 5 | 75.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s809-nr | 1,000,000 | 9 | 100.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s809-nr | 1,000,000 | 5 | 89.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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