NREL's S802 Airfoil (s802-nr)
NREL's S802 Airfoil - NREL HAWT airfoil S802 tip Not recommended
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(s802-nr) NREL's S802 Airfoil NREL HAWT airfoil S802 tip Not recommended Max thickness 11.5% at 37.9% chord. Max camber 3.8% at 47.3% chord Source NWTC National WInd Technology Center Source dat file The dat file is in Selig format |
NREL's S802 Airfoil x/c y/c 1.00000 0.00000 0.99666 0.00105 0.98730 0.00427 0.97302 0.00923 0.95416 0.01500 0.93048 0.02120 0.90208 0.02796 0.86941 0.03531 0.83300 0.04314 0.79337 0.05129 0.75111 0.05957 0.70680 0.06774 0.66104 0.07551 0.61441 0.08255 0.56748 0.08838 0.52044 0.09240 0.47311 0.09451 0.42569 0.09504 0.37871 0.09421 0.33264 0.09212 0.28798 0.08885 0.24520 0.08451 0.20474 0.07918 0.16702 0.07297 0.13242 0.06598 0.10132 0.05833 0.07401 0.05015 0.05078 0.04156 0.03182 0.03269 0.01729 0.02369 0.00724 0.01471 0.00153 0.00605 0.00000 0.00000 0.00014 -0.00164 0.00397 -0.00754 0.01367 -0.01210 0.02895 -0.01600 0.04956 -0.01913 0.07528 -0.02152 0.10587 -0.02318 0.14099 -0.02415 0.18029 -0.02450 0.22333 -0.02431 0.26960 -0.02365 0.31857 -0.02259 0.36963 -0.02117 0.42216 -0.01945 0.47551 -0.01744 0.52901 -0.01512 0.58198 -0.01237 0.63388 -0.00891 0.68470 -0.00444 0.73467 0.00047 0.78328 0.00483 0.82950 0.00798 0.87227 0.00955 0.91038 0.00932 0.94251 0.00756 0.96777 0.00501 0.98575 0.00250 0.99646 0.00067 1.00000 0.00000 |
Dat file parser warnings
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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 S802 Airfoil (s802-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s802-nr | 50,000 | 9 | 36.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s802-nr | 50,000 | 5 | 33.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s802-nr | 100,000 | 9 | 61 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s802-nr | 100,000 | 5 | 60.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s802-nr | 200,000 | 9 | 91.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s802-nr | 200,000 | 5 | 85.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s802-nr | 500,000 | 9 | 124.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s802-nr | 500,000 | 5 | 113.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s802-nr | 1,000,000 | 9 | 149.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s802-nr | 1,000,000 | 5 | 132.5 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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