NREL's S814 Airfoil (s814-nr)
NREL's S814 Airfoil - NREL HAWT airfoil S814 root 24.0% Dia=20 to 30 m Re=1.5E+6 Clmax(S)=1.56 Clmax(R)=1.51 High max lift coef
| Details | Dat file | Parser | |
|
(s814-nr) NREL's S814 Airfoil NREL HAWT airfoil S814 root 24.0% Dia=20 to 30 m Re=1.5E+6 Clmax(S)=1.56 Clmax(R)=1.51 High max lift coef Max thickness 24.1% at 28.4% chord. Max camber 3% at 74.5% chord Source NWTC National WInd Technology Center Source dat file The dat file is in Selig format |
NREL's S814 Airfoil x/c y/c 1.000000 0.000000 0.996277 0.001079 0.985681 0.004644 0.969429 0.010691 0.948574 0.018525 0.923625 0.027157 0.894505 0.035738 0.860850 0.044178 0.823023 0.052748 0.781586 0.061424 0.737130 0.070108 0.690273 0.078659 0.641651 0.086901 0.591910 0.094633 0.541692 0.101631 0.491625 0.107648 0.442317 0.112418 0.394345 0.115645 0.348257 0.116962 0.304384 0.115627 0.261983 0.111612 0.221337 0.105629 0.182903 0.097997 0.147112 0.088966 0.114367 0.078763 0.085039 0.067619 0.059481 0.055766 0.038007 0.043458 0.020952 0.030954 0.008577 0.018556 0.001431 0.006672 0.001119 0.005797 0.000338 0.002959 0.000002 0.000223 0.000245 -0.002549 0.000678 -0.004584 0.000925 -0.005491 0.006381 -0.017430 0.016792 -0.031576 0.031367 -0.046492 0.049641 -0.061655 0.071240 -0.076713 0.095610 -0.091093 0.122438 -0.104309 0.151203 -0.115726 0.181669 -0.124578 0.213672 -0.130235 0.247139 -0.131310 0.283942 -0.127757 0.323782 -0.120293 0.367326 -0.109093 0.414593 -0.095249 0.465255 -0.079660 0.518814 -0.063236 0.574574 -0.046894 0.631638 -0.031520 0.688908 -0.017904 0.745125 -0.006688 0.798908 0.001698 0.848830 0.007070 0.893492 0.009517 0.931609 0.009395 0.962086 0.007279 0.983819 0.003889 0.996132 0.001014 1.000000 0.000000 |
Dat file parser warnings
|
Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file |
Similar airfoils
|
Polars for NREL's S814 Airfoil (s814-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s814-nr | 50,000 | 9 | 4.4 at α=14.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s814-nr | 50,000 | 5 | 10.9 at α=14° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s814-nr | 100,000 | 9 | 35.2 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s814-nr | 100,000 | 5 | 40.1 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s814-nr | 200,000 | 9 | 58.3 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s814-nr | 200,000 | 5 | 58.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s814-nr | 500,000 | 9 | 84.4 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s814-nr | 500,000 | 5 | 80.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s814-nr | 1,000,000 | 9 | 104.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s814-nr | 1,000,000 | 5 | 97.1 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||