NREL's S806A Airfoil (modified line 35) (s806a-nr)
NREL's S806A Airfoil (modified line 35) - NREL HAWT airfoil S806A tip
| Details | Dat file | Parser | |
|
(s806a-nr) NREL's S806A Airfoil (modified line 35) NREL HAWT airfoil S806A tip Max thickness 11.5% at 45% chord. Max camber 2.8% at 45% chord Source NWTC National WInd Technology Center Source dat file The dat file is in Selig format |
NREL's S806A Airfoil (modified line 35) x/c y/c 1.00000 0.00000 0.97998 0.00677 0.95995 0.00940 0.93994 0.01206 0.91994 0.01484 0.90000 0.01795 0.85000 0.02791 0.80000 0.03813 0.75000 0.04853 0.70002 0.05874 0.65003 0.06795 0.60002 0.07532 0.55001 0.08058 0.50000 0.08372 0.45000 0.08496 0.40000 0.08464 0.35000 0.08293 0.29999 0.07985 0.24999 0.07535 0.19998 0.06924 0.14999 0.06120 0.11998 0.05520 0.09996 0.05055 0.07997 0.04524 0.06000 0.03905 0.04992 0.03548 0.03999 0.03154 0.02990 0.02695 0.01990 0.02161 0.00998 0.01470 0.00271 0.00691 0.00000 0.00000 0.00000 -0.00021 0.00297 -0.00550 0.01002 -0.00889 0.01997 -0.01159 0.02998 -0.01377 0.03998 -0.01533 0.05000 -0.01659 0.05999 -0.01772 0.07999 -0.01965 0.10000 -0.02120 0.12000 -0.02252 0.15000 -0.02419 0.20000 -0.02634 0.25000 -0.02792 0.30000 -0.02903 0.35000 -0.02971 0.40000 -0.03000 0.45000 -0.02993 0.50000 -0.02949 0.55000 -0.02867 0.60000 -0.02745 0.65000 -0.02575 0.70001 -0.02340 0.75001 -0.02021 0.80000 -0.01621 0.85000 -0.01166 0.90000 -0.00686 0.91998 -0.00592 0.93998 -0.00540 0.95999 -0.00500 0.98000 -0.00462 1.00000 0.00000 |
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 S806A Airfoil (modified line 35) (s806a-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s806a-nr | 50,000 | 9 | 34.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s806a-nr | 100,000 | 9 | 53.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s806a-nr | 200,000 | 9 | 76.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s806a-nr | 500,000 | 9 | 107.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s806a-nr | 1,000,000 | 9 | 119.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| Reynolds number calculator | |||||||