NREL's S826 Airfoil (s826-nr)
NREL's S826 Airfoil - NREL HAWT airfoil S826 tip 14.0% Dia=20 to 40 m Re=1.5E+6 Clmax(S)=1.42 Clmax(R)=1.31 High max lift coef
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(s826-nr) NREL's S826 Airfoil NREL HAWT airfoil S826 tip 14.0% Dia=20 to 40 m Re=1.5E+6 Clmax(S)=1.42 Clmax(R)=1.31 High max lift coef Max thickness 14% at 33.7% chord. Max camber 4.3% at 62% chord Source NWTC National WInd Technology Center Source dat file The dat file is in Selig format |
NREL's S826 Airfoil x/c y/c 1.000000 0.000000 0.996640 0.000985 0.987056 0.004265 0.972314 0.009834 0.953332 0.017037 0.930531 0.024949 0.903794 0.032768 0.872736 0.040403 0.837646 0.048100 0.799007 0.055842 0.757330 0.063544 0.713160 0.071084 0.667064 0.078312 0.619624 0.085056 0.571426 0.091118 0.523051 0.096277 0.475063 0.100280 0.428007 0.102811 0.382245 0.103258 0.337323 0.101581 0.293568 0.098300 0.251455 0.093644 0.211424 0.087785 0.173909 0.080881 0.139301 0.073078 0.107962 0.064532 0.080220 0.055386 0.056312 0.045810 0.036491 0.035989 0.020843 0.026134 0.009548 0.016553 0.002548 0.007584 0.000169 0.001654 0.000001 0.000102 0.000000 0.000006 0.000198 -0.001417 0.000946 -0.002691 0.002165 -0.003992 0.003667 -0.005223 0.013639 -0.010342 0.029183 -0.015169 0.049938 -0.019578 0.075768 -0.023565 0.106324 -0.027219 0.141288 -0.030720 0.179884 -0.034729 0.220074 -0.038653 0.261526 -0.040769 0.304974 -0.040625 0.350096 -0.038079 0.397636 -0.032821 0.447637 -0.025646 0.500087 -0.017114 0.554624 -0.008267 0.610364 0.000049 0.666289 0.007219 0.721305 0.012793 0.774276 0.016474 0.824060 0.018113 0.869551 0.017689 0.909558 0.015218 0.942700 0.011278 0.968241 0.006966 0.986101 0.003275 0.996568 0.000850 1.000000 0.000000 |
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Similar airfoils
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Polars for NREL's S826 Airfoil (s826-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s826-nr | 50,000 | 9 | 34.6 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s826-nr | 50,000 | 5 | 34.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s826-nr | 100,000 | 9 | 60.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s826-nr | 100,000 | 5 | 60 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s826-nr | 200,000 | 9 | 83 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s826-nr | 200,000 | 5 | 81.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s826-nr | 500,000 | 9 | 114 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s826-nr | 500,000 | 5 | 107.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s826-nr | 1,000,000 | 9 | 137.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s826-nr | 1,000,000 | 5 | 126.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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