Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
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(s816-nr) NREL's S816 Airfoil | NREL HAWT airfoil S816 primary 21.0% Dia=30 to 50 m Re=4.0E+6 Clmax(S)=1.20 Clmax(R)=1.17 Restrained max lift coef Max thickness 21% at 39% chord Max camber 1.8% at 67.6% chord | Remove Airfoil details Airfoil plotter |
(sc20010-il) NASA SC(2)-0010 AIRFOIL | NASA SC(2)-0010 airfoil (NASA TP-2969) Max thickness 10% at 37% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(fx84w127-il) FX 84-W-127 | Wortmann FX 84-W-127 airfoil for use on wind turbines (W) Max thickness 12.8% at 33.9% chord Max camber 3.7% at 40.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s816-nr,sc20010-il,fx84w127-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s816-nr | 50,000 | 9 | 16.9 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s816-nr | 50,000 | 5 | 12.9 at α=12.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s816-nr | 100,000 | 9 | 21 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s816-nr | 100,000 | 5 | 22.2 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s816-nr | 200,000 | 9 | 59 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s816-nr | 200,000 | 5 | 60.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s816-nr | 500,000 | 9 | 96.9 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s816-nr | 500,000 | 5 | 91 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s816-nr | 1,000,000 | 9 | 121.4 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s816-nr | 1,000,000 | 5 | 108.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20010-il | 50,000 | 9 | 23.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20010-il | 50,000 | 5 | 22.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20010-il | 100,000 | 9 | 33.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20010-il | 100,000 | 5 | 28.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20010-il | 200,000 | 9 | 39.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20010-il | 200,000 | 5 | 39 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20010-il | 500,000 | 9 | 52 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20010-il | 500,000 | 5 | 56.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20010-il | 1,000,000 | 9 | 67.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20010-il | 1,000,000 | 5 | 70.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx84w127-il | 50,000 | 9 | 25.8 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx84w127-il | 50,000 | 5 | 24.3 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx84w127-il | 100,000 | 9 | 53.8 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx84w127-il | 100,000 | 5 | 54.8 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx84w127-il | 200,000 | 9 | 80.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx84w127-il | 200,000 | 5 | 79.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx84w127-il | 500,000 | 9 | 115.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx84w127-il | 500,000 | 5 | 110.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx84w127-il | 1,000,000 | 9 | 142.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx84w127-il | 1,000,000 | 5 | 131.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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