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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(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 |
(sc20706-il) NASA SC(2)-0706 AIRFOIL | NASA SC(2)-0706 airfoil (NASA TP-2969) Max thickness 6% at 34% chord Max camber 1.6% at 82% chord | Remove Airfoil details Airfoil plotter |
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Polars for (s7055-il,sc20706-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| sc20706-il | 50,000 | 9 | 24 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20706-il | 50,000 | 5 | 25.3 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20706-il | 100,000 | 9 | 38.2 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20706-il | 100,000 | 5 | 33.3 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20706-il | 200,000 | 9 | 40.6 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20706-il | 200,000 | 5 | 44.1 at α=0.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20706-il | 500,000 | 9 | 67 at α=0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20706-il | 500,000 | 5 | 55.8 at α=-0.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sc20706-il | 1,000,000 | 9 | 96.6 at α=-0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sc20706-il | 1,000,000 | 5 | 68 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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