NREL's S831 Airfoil (s831-nr)
NREL's S831 Airfoil - NREL HAWT airfoil S831 tip 18.0% Dia=40 to 50 m Re=3.5E+6 Clmax(S)=1.50 Clmax(R)=1.48 High max lift coef
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(s831-nr) NREL's S831 Airfoil NREL HAWT airfoil S831 tip 18.0% Dia=40 to 50 m Re=3.5E+6 Clmax(S)=1.50 Clmax(R)=1.48 High max lift coef Max thickness 18% at 44.2% chord. Max camber 5% at 53.1% chord Source NWTC National WInd Technology Center Source dat file The dat file is in Selig format |
NREL's S831 Airfoil x/c y/c 1.000000 0.000000 0.996135 0.001055 0.985140 0.004813 0.968342 0.011573 0.946987 0.020825 0.921802 0.031665 0.892944 0.043266 0.860354 0.055441 0.824598 0.068183 0.786318 0.081159 0.746095 0.093944 0.704447 0.106077 0.661848 0.117074 0.618711 0.126403 0.575223 0.133491 0.531374 0.137989 0.487067 0.139780 0.442228 0.139168 0.397275 0.136586 0.352693 0.132262 0.308992 0.126384 0.266627 0.119119 0.226079 0.110644 0.187765 0.101132 0.152120 0.090773 0.119511 0.079753 0.090311 0.068282 0.064830 0.056552 0.043333 0.044786 0.026064 0.033188 0.013075 0.022006 0.004490 0.011683 0.000358 0.002767 0.000044 0.000883 0.000042 -0.000801 0.000170 -0.001549 0.000408 -0.002208 0.000798 -0.002808 0.001343 -0.003400 0.002797 -0.004575 0.009658 -0.007951 0.024215 -0.011696 0.045249 -0.014798 0.072290 -0.017961 0.104406 -0.021314 0.141046 -0.024794 0.181460 -0.028309 0.225087 -0.031714 0.271224 -0.034849 0.319288 -0.037521 0.368594 -0.039511 0.418547 -0.040536 0.468500 -0.040128 0.518467 -0.037670 0.568613 -0.033262 0.618885 -0.027181 0.669241 -0.019934 0.719339 -0.012257 0.768650 -0.004920 0.816389 0.001180 0.861302 0.005304 0.901930 0.007074 0.936659 0.006680 0.964289 0.004890 0.984164 0.002634 0.996059 0.000768 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 S831 Airfoil (s831-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s831-nr | 50,000 | 9 | 17.2 at α=13.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s831-nr | 50,000 | 5 | 14.2 at α=13.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s831-nr | 100,000 | 9 | 21.8 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s831-nr | 100,000 | 5 | 21.2 at α=12.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s831-nr | 200,000 | 9 | 36.7 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s831-nr | 200,000 | 5 | 47 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s831-nr | 500,000 | 9 | 113.9 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s831-nr | 500,000 | 5 | 112.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s831-nr | 1,000,000 | 9 | 152.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s831-nr | 1,000,000 | 5 | 147.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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