NREL's S821 Airfoil (s821-nr)
NREL's S821 Airfoil - NREL HAWT airfoil S821 root 24.0% Dia=10 to 20 m Re=8.0E+5 Clmax(S)=1.40 Clmax(R)=1.35 Restrained max lift coef
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(s821-nr) NREL's S821 Airfoil NREL HAWT airfoil S821 root 24.0% Dia=10 to 20 m Re=8.0E+5 Clmax(S)=1.40 Clmax(R)=1.35 Restrained max lift coef Max thickness 24.2% at 24.6% chord. Max camber 2.6% at 77.6% chord Source NWTC National WInd Technology Center Source dat file The dat file is in Selig format |
NREL's S821 Airfoil x/c y/c 1.000000 0.000000 0.996211 0.000979 0.985369 0.004273 0.968663 0.009953 0.947175 0.017397 0.921468 0.025654 0.891519 0.033883 0.857009 0.041987 0.818334 0.050225 0.776090 0.058556 0.730890 0.066851 0.683359 0.074932 0.634121 0.082589 0.583790 0.089594 0.532956 0.095710 0.482180 0.100704 0.431988 0.104359 0.382867 0.106477 0.335265 0.106891 0.289592 0.105457 0.246159 0.101964 0.204936 0.096534 0.166314 0.089543 0.130747 0.081197 0.098642 0.071677 0.070407 0.061141 0.046352 0.049758 0.026874 0.037691 0.012130 0.025117 0.004030 0.014909 0.002683 0.012510 0.002318 0.011776 0.001068 0.008667 0.000364 0.005418 0.000040 0.001941 0.000007 -0.000841 0.002499 -0.016695 0.008996 -0.034096 0.018943 -0.052456 0.031877 -0.070873 0.047652 -0.088744 0.065953 -0.105342 0.086614 -0.119982 0.109606 -0.131602 0.135542 -0.139985 0.164146 -0.144525 0.196445 -0.145040 0.232413 -0.142078 0.271925 -0.135855 0.314875 -0.126633 0.361129 -0.114780 0.410491 -0.100789 0.462665 -0.085271 0.517218 -0.068945 0.573551 -0.052597 0.630881 -0.037031 0.688228 -0.023015 0.744435 -0.011208 0.798205 -0.002094 0.848154 0.004073 0.892896 0.007306 0.931134 0.007903 0.961748 0.006400 0.983628 0.003499 0.996079 0.000922 1.000000 0.000000 |
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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 S821 Airfoil (s821-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s821-nr | 50,000 | 9 | 4.8 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s821-nr | 50,000 | 5 | 19.4 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s821-nr | 100,000 | 9 | 35.6 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s821-nr | 100,000 | 5 | 37.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s821-nr | 200,000 | 9 | 52.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s821-nr | 200,000 | 5 | 51.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s821-nr | 500,000 | 9 | 72.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s821-nr | 500,000 | 5 | 66 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s821-nr | 1,000,000 | 9 | 87.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s821-nr | 1,000,000 | 5 | 75.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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