NREL's S829 Airfoil (s829-nr)
NREL's S829 Airfoil - NREL HAWT airfoil S829 tip 16.0% Dia=20 to 40 m Re=2.0E+6 Clmax(S)=0.70 Clmax(R)=0.68 Restrained max lift coef
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(s829-nr) NREL's S829 Airfoil NREL HAWT airfoil S829 tip 16.0% Dia=20 to 40 m Re=2.0E+6 Clmax(S)=0.70 Clmax(R)=0.68 Restrained max lift coef Max thickness 16% at 48.3% chord. Max camber 0.7% at 48.3% chord Source NWTC National WInd Technology Center Source dat file The dat file is in Selig format |
NREL's S829 Airfoil x/c y/c 1.000000 0.000000 0.995908 0.000184 0.983952 0.001451 0.965020 0.004552 0.940227 0.009705 0.910603 0.016689 0.876933 0.025073 0.839824 0.034535 0.800071 0.044742 0.758431 0.055135 0.715519 0.064992 0.671626 0.073541 0.626802 0.080193 0.580845 0.084567 0.533523 0.087003 0.485305 0.087935 0.436759 0.087540 0.388426 0.085941 0.340865 0.083244 0.294603 0.079547 0.250182 0.074947 0.208099 0.069533 0.168842 0.063402 0.132850 0.056645 0.100532 0.049368 0.072257 0.041673 0.048331 0.033676 0.029058 0.025463 0.014499 0.017185 0.004915 0.009131 0.000687 0.002799 0.000298 0.001695 0.000148 0.001107 0.000023 -0.000427 0.000469 -0.001921 0.001361 -0.003523 0.002135 -0.004596 0.010086 -0.011696 0.023141 -0.018955 0.041281 -0.026113 0.064230 -0.033011 0.091829 -0.039542 0.123746 -0.045653 0.159638 -0.051272 0.199090 -0.056344 0.241652 -0.060807 0.286841 -0.064613 0.334124 -0.067702 0.382968 -0.070023 0.432791 -0.071515 0.483034 -0.072111 0.533112 -0.071744 0.582463 -0.070329 0.630507 -0.067742 0.676785 -0.063696 0.721212 -0.058010 0.763759 -0.050820 0.804383 -0.042496 0.842871 -0.033601 0.878852 -0.024774 0.911728 -0.016650 0.940830 -0.009764 0.965297 -0.004631 0.984045 -0.001508 0.995921 -0.000204 1.000000 0.000000 |
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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 S829 Airfoil (s829-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s829-nr | 50,000 | 9 | 22.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s829-nr | 50,000 | 5 | 21 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s829-nr | 100,000 | 9 | 33.1 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s829-nr | 100,000 | 5 | 25.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s829-nr | 200,000 | 9 | 47.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s829-nr | 200,000 | 5 | 35.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s829-nr | 500,000 | 9 | 63 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s829-nr | 500,000 | 5 | 62.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s829-nr | 1,000,000 | 9 | 88.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s829-nr | 1,000,000 | 5 | 72.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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