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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(sc20404-il) NASA SC(2)-0404 AIRFOIL | NASA SC(2)-0404 airfoil (NASA TP-2969) Max thickness 4% at 37% chord Max camber 0.7% at 81% chord | Remove Airfoil details Airfoil plotter |
(s804-nr) NREL's S804 Airfoil | NREL HAWT airfoil S804 root Not recommended Max thickness 17.9% at 26.7% chord Max camber 4.2% at 39.6% chord | Remove Airfoil details Airfoil plotter |
(s828-nr) NREL's S828 Airfoil | NREL HAWT airfoil S828 tip 16.0% Dia=40 to 50 m Re=3.0E+6 Clmax(S)=0.90 Clmax(R)=0.89 Restrained max lift coef Max thickness 16% at 47.1% chord Max camber 2.2% at 47.1% chord | Remove Airfoil details Airfoil plotter |
(s7055-il) S7055 (10.5%) Flat-Bottomed | Selig S7055 low Reynolds number airfoil Max thickness 10.5% at 31.8% chord Max camber 3.3% at 38.6% chord | Remove Airfoil details Airfoil plotter |
(sc20712-il) NASA SC(2)-0712 AIRFOIL | NASA SC(2)-0712 airfoil (NASA TP-2969) Max thickness 12% at 37% chord Max camber 2.2% at 81% chord | Remove Airfoil details Airfoil plotter |
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Polars for (sc20404-il,s804-nr,s828-nr,s7055-il,sc20712-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sc20404-il | 50,000 | 9 | 20.7 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20404-il | 50,000 | 5 | 19.1 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20404-il | 100,000 | 9 | 37.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20404-il | 100,000 | 5 | 26 at α=1.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20404-il | 200,000 | 9 | 35.2 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20404-il | 200,000 | 5 | 35.2 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20404-il | 500,000 | 9 | 52 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20404-il | 500,000 | 5 | 41.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20404-il | 1,000,000 | 9 | 49.7 at α=0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20404-il | 1,000,000 | 5 | 55.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s804-nr | 50,000 | 9 | 4.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s804-nr | 50,000 | 5 | 22.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s804-nr | 100,000 | 9 | 28.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s804-nr | 100,000 | 5 | 45.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s804-nr | 200,000 | 9 | 58.2 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s804-nr | 200,000 | 5 | 67.9 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s804-nr | 500,000 | 9 | 98.1 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s804-nr | 500,000 | 5 | 98.6 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s804-nr | 1,000,000 | 9 | 128 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s804-nr | 1,000,000 | 5 | 125.5 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s828-nr | 50,000 | 9 | 19.8 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s828-nr | 50,000 | 5 | 18.1 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s828-nr | 100,000 | 9 | 28.9 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s828-nr | 100,000 | 5 | 28.5 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s828-nr | 200,000 | 9 | 63.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s828-nr | 200,000 | 5 | 40.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s828-nr | 500,000 | 9 | 76.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s828-nr | 500,000 | 5 | 82 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s828-nr | 1,000,000 | 9 | 112.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s828-nr | 1,000,000 | 5 | 107 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s7055-il | 50,000 | 9 | 31.1 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7055-il | 50,000 | 5 | 36.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s7055-il | 100,000 | 9 | 54.3 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7055-il | 100,000 | 5 | 56.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s7055-il | 200,000 | 9 | 77.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7055-il | 200,000 | 5 | 75.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s7055-il | 500,000 | 9 | 107.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7055-il | 500,000 | 5 | 99.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s7055-il | 1,000,000 | 9 | 129.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s7055-il | 1,000,000 | 5 | 116.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20712-il | 50,000 | 9 | 24.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20712-il | 50,000 | 5 | 23.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20712-il | 100,000 | 9 | 32 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20712-il | 100,000 | 5 | 33.4 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20712-il | 200,000 | 9 | 43.5 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20712-il | 200,000 | 5 | 47.4 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20712-il | 500,000 | 9 | 70.6 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20712-il | 500,000 | 5 | 64.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20712-il | 1,000,000 | 9 | 85.3 at α=-0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20712-il | 1,000,000 | 5 | 80.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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