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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(s808-nr) NREL's S808 Airfoil | NREL HAWT airfoil S808 root Max thickness 21% at 24.4% chord Max camber 2.4% at 72.9% chord | Remove Airfoil details Airfoil plotter |
(sc20406-il) NASA SC(2)-0406 AIRFOIL | NASA SC(2)-0406 airfoil (NASA TP-2969) Max thickness 6% at 35% chord Max camber 0.6% at 79% chord | Remove Airfoil details Airfoil plotter |
(s807-nr) NREL's S807 Airfoil | NREL HAWT airfoil S807 root Max thickness 18% at 28.7% chord Max camber 1.9% at 78.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s808-nr,sc20406-il,s807-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s808-nr | 50,000 | 9 | 8.2 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s808-nr | 50,000 | 5 | 24.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s808-nr | 100,000 | 9 | 36.5 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s808-nr | 100,000 | 5 | 41.4 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s808-nr | 200,000 | 9 | 55.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s808-nr | 200,000 | 5 | 56 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s808-nr | 500,000 | 9 | 78.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s808-nr | 500,000 | 5 | 76.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s808-nr | 1,000,000 | 9 | 98.5 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s808-nr | 1,000,000 | 5 | 92.8 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20406-il | 50,000 | 9 | 20.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20406-il | 50,000 | 5 | 24.5 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20406-il | 100,000 | 9 | 37.2 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20406-il | 100,000 | 5 | 32.3 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20406-il | 200,000 | 9 | 47.5 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20406-il | 200,000 | 5 | 36.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20406-il | 500,000 | 9 | 52.9 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20406-il | 500,000 | 5 | 50.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20406-il | 1,000,000 | 9 | 59.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20406-il | 1,000,000 | 5 | 61.5 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s807-nr | 50,000 | 9 | 20.3 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s807-nr | 50,000 | 5 | 22 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s807-nr | 100,000 | 9 | 33.4 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s807-nr | 100,000 | 5 | 40.3 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s807-nr | 200,000 | 9 | 56.4 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s807-nr | 200,000 | 5 | 59.4 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s807-nr | 500,000 | 9 | 84.9 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s807-nr | 500,000 | 5 | 83.9 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s807-nr | 1,000,000 | 9 | 106.7 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s807-nr | 1,000,000 | 5 | 101.7 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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