NREL's S822 Airfoil (s822-nr)
NREL's S822 Airfoil - NREL HAWT airfoil S822 tip 16.0% Dia=2 to 10 m Re=6.0E+5 Clmax(S)=1.00 Clmax(R)=0.98 Restrained max lift coef
| Details | Dat file | Parser | |
|
(s822-nr) NREL's S822 Airfoil NREL HAWT airfoil S822 tip 16.0% Dia=2 to 10 m Re=6.0E+5 Clmax(S)=1.00 Clmax(R)=0.98 Restrained max lift coef Max thickness 16% at 39.2% chord. Max camber 1.8% at 59.5% chord Source NWTC National WInd Technology Center Source dat file The dat file is in Selig format |
NREL's S822 Airfoil x/c y/c 1.000000 0.000000 0.996089 0.000642 0.985048 0.003157 0.968133 0.007602 0.946046 0.013324 0.918825 0.020084 0.887037 0.028045 0.851444 0.037037 0.812782 0.046731 0.771742 0.056677 0.728946 0.066315 0.684771 0.074819 0.638946 0.081988 0.591971 0.087923 0.544321 0.092477 0.496467 0.095295 0.448320 0.096342 0.400324 0.095949 0.353012 0.094259 0.306932 0.091363 0.262594 0.087322 0.220471 0.082211 0.181021 0.076101 0.144635 0.069084 0.111706 0.061261 0.082528 0.052754 0.057423 0.043713 0.036592 0.034302 0.020310 0.024706 0.008599 0.015142 0.001760 0.006074 0.000651 0.003396 0.000138 0.001358 0.000023 -0.000542 0.000294 -0.001935 0.000443 -0.002413 0.001282 -0.004385 0.005329 -0.010118 0.015376 -0.018680 0.030216 -0.027173 0.049559 -0.035201 0.073374 -0.042563 0.101374 -0.049059 0.133441 -0.054581 0.169219 -0.059031 0.208482 -0.062361 0.250797 -0.064545 0.295834 -0.065585 0.343087 -0.065504 0.392138 -0.064340 0.442420 -0.062144 0.493444 -0.058965 0.544594 -0.054833 0.595407 -0.049596 0.645795 -0.043462 0.695149 -0.036874 0.742856 -0.030066 0.788279 -0.023032 0.831428 -0.016082 0.871626 -0.010003 0.907952 -0.005223 0.939440 -0.001945 0.965150 -0.000135 0.984246 0.000448 0.996022 0.000259 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 S822 Airfoil (s822-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s822-nr | 50,000 | 9 | 27.7 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s822-nr | 50,000 | 5 | 23.7 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s822-nr | 100,000 | 9 | 42.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s822-nr | 100,000 | 5 | 39.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s822-nr | 200,000 | 9 | 68.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s822-nr | 200,000 | 5 | 60.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s822-nr | 500,000 | 9 | 94.7 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s822-nr | 500,000 | 5 | 85.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s822-nr | 1,000,000 | 9 | 117.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s822-nr | 1,000,000 | 5 | 96.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||