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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(s4083-il) S4083 (8%) | Selig S4083 low Reynolds number airfoil Max thickness 8% at 22.5% chord Max camber 3.4% at 35.5% chord | Remove Airfoil details Airfoil plotter |
(s820-nr) NREL's S820 Airfoil | NREL HAWT airfoil S820 tip 16.0% Dia=10 to 20 m Re=1.3E+6 Clmax(S)=1.10 Clmax(R)=1.06 Restrained max lift coef Max thickness 16% at 45.1% chord Max camber 2.1% at 59.7% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s4083-il,s820-nr)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| s4083-il | 50,000 | 9 | 31.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4083-il | 50,000 | 5 | 38.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4083-il | 100,000 | 9 | 51.8 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4083-il | 100,000 | 5 | 56.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4083-il | 200,000 | 9 | 73.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4083-il | 200,000 | 5 | 74.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4083-il | 500,000 | 9 | 102.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4083-il | 500,000 | 5 | 98.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s4083-il | 1,000,000 | 9 | 124.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s4083-il | 1,000,000 | 5 | 115.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s820-nr | 50,000 | 9 | 26.8 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s820-nr | 50,000 | 5 | 22.4 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s820-nr | 100,000 | 9 | 39.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s820-nr | 100,000 | 5 | 37 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s820-nr | 200,000 | 9 | 65.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s820-nr | 200,000 | 5 | 65.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s820-nr | 500,000 | 9 | 105.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s820-nr | 500,000 | 5 | 95.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s820-nr | 1,000,000 | 9 | 129.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s820-nr | 1,000,000 | 5 | 109.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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