NREL's S827 Airfoil (s827-nr)
NREL's S827 Airfoil - NREL HAWT airfoil S827 primary 21.0% Dia=40 to 50 m Re=4.0E+6 Clmax(S)=1.00 Clmax(R)=0.99 Restrained max lift coef
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(s827-nr) NREL's S827 Airfoil NREL HAWT airfoil S827 primary 21.0% Dia=40 to 50 m Re=4.0E+6 Clmax(S)=1.00 Clmax(R)=0.99 Restrained max lift coef Max thickness 21% at 44.9% chord. Max camber 2.2% at 68% chord Source NWTC National WInd Technology Center Source dat file The dat file is in Selig format |
NREL's S827 Airfoil x/c y/c 1.000000 0.000000 0.995865 0.000688 0.983991 0.003462 0.965623 0.008883 0.942076 0.016761 0.914301 0.026439 0.882774 0.037198 0.847739 0.048750 0.809883 0.060923 0.769919 0.073258 0.728467 0.085200 0.686063 0.096134 0.643172 0.105349 0.599873 0.111666 0.554955 0.115129 0.508787 0.116559 0.461905 0.116215 0.414850 0.114263 0.368130 0.110840 0.322276 0.106079 0.277778 0.100112 0.235151 0.093080 0.194854 0.085118 0.157351 0.076379 0.123048 0.067010 0.092339 0.057184 0.065565 0.047070 0.043030 0.036866 0.025012 0.026767 0.011673 0.017028 0.003275 0.008024 0.000399 0.002378 0.000036 0.000634 0.000013 0.000352 0.000003 -0.000165 0.000095 -0.000897 0.000363 -0.001597 0.000778 -0.002319 0.001965 -0.003820 0.003899 -0.005651 0.014437 -0.012259 0.030681 -0.019044 0.052502 -0.025920 0.079539 -0.032959 0.111405 -0.040201 0.147601 -0.047819 0.187347 -0.055799 0.229976 -0.064258 0.274275 -0.072950 0.319371 -0.081817 0.363258 -0.089640 0.405999 -0.094098 0.449111 -0.094786 0.492458 -0.091610 0.537389 -0.084728 0.583845 -0.075473 0.631390 -0.064654 0.679501 -0.053010 0.727544 -0.041261 0.774753 -0.030101 0.820228 -0.020155 0.862940 -0.011936 0.901760 -0.005792 0.935492 -0.001822 0.963007 0.000174 0.983348 0.000661 0.995812 0.000321 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 S827 Airfoil (s827-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s827-nr | 50,000 | 9 | 16.5 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s827-nr | 50,000 | 5 | 14 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s827-nr | 100,000 | 9 | 20.4 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s827-nr | 100,000 | 5 | 21.3 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s827-nr | 200,000 | 9 | 35.6 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s827-nr | 200,000 | 5 | 35 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s827-nr | 500,000 | 9 | 84.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s827-nr | 500,000 | 5 | 81.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s827-nr | 1,000,000 | 9 | 121.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s827-nr | 1,000,000 | 5 | 109.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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