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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(e178-il) E178 (8.69%) | Eppler E178 low Reynolds number airfoil Max thickness 8.7% at 29.8% chord Max camber 2.8% at 38.8% chord | Remove Airfoil details Airfoil plotter |
(s1016-il) S1016 | Selig S1016 HPV airfoil Max thickness 17.5% at 41.8% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(tsagi12-il) TSAGI 12% AIRFOIL | TSAGI 12% airfoil Max thickness 11.9% at 30% chord Max camber 2% at 30% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e178-il,s1016-il,tsagi12-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e178-il | 50,000 | 9 | 36.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e178-il | 50,000 | 5 | 37.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e178-il | 100,000 | 9 | 56.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e178-il | 100,000 | 5 | 55.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e178-il | 200,000 | 9 | 77.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e178-il | 200,000 | 5 | 73.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e178-il | 500,000 | 9 | 105 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e178-il | 500,000 | 5 | 95.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e178-il | 1,000,000 | 9 | 125.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e178-il | 1,000,000 | 5 | 108.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1016-il | 50,000 | 9 | 28.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1016-il | 50,000 | 5 | 22.4 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1016-il | 100,000 | 9 | 39.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1016-il | 100,000 | 5 | 23.5 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1016-il | 200,000 | 9 | 35.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1016-il | 200,000 | 5 | 30.2 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1016-il | 500,000 | 9 | 40.1 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1016-il | 500,000 | 5 | 41.8 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| s1016-il | 1,000,000 | 9 | 52.2 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| s1016-il | 1,000,000 | 5 | 52 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tsagi12-il | 50,000 | 9 | 31.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tsagi12-il | 50,000 | 5 | 32.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tsagi12-il | 100,000 | 9 | 49.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tsagi12-il | 100,000 | 5 | 49.7 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tsagi12-il | 200,000 | 9 | 66.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tsagi12-il | 200,000 | 5 | 65.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tsagi12-il | 500,000 | 9 | 88.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tsagi12-il | 500,000 | 5 | 76.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tsagi12-il | 1,000,000 | 9 | 91.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tsagi12-il | 1,000,000 | 5 | 86.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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