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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(ah80140-il) AH 80-140 | Althaus AH 80-140 airfoil Max thickness 14% at 30.9% chord Max camber 4.4% at 33.9% chord | Remove Airfoil details Airfoil plotter |
(ag14-il) AG14 | Drela AG14 airfoil Max thickness 5.4% at 19.9% chord Max camber 2% at 41.9% chord | Remove Airfoil details Airfoil plotter |
(e186-il) E186 (10.27%) | Eppler E186 low Reynolds number airfoil Max thickness 10.2% at 29% chord Max camber 0.8% at 29% chord | Remove Airfoil details Airfoil plotter |
(ag12-il) AG12 | Drela AG12 airfoil Max thickness 6.2% at 20.8% chord Max camber 1.8% at 42.8% chord | Remove Airfoil details Airfoil plotter |
(ah21-9-il) AH21 9% version (Andrew Hollom) | Andrew Hollom AH 21 airfoil (original 9% version) Max thickness 7% at 34.9% chord Max camber 1.8% at 54.8% chord | Remove Airfoil details Airfoil plotter |
(ag18-il) AG18 | Drela AG18 airfoil Max thickness 5.9% at 20.7% chord Max camber 2.2% at 44.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ah80140-il,ag14-il,e186-il,ag12-il,ah21-9-il,ag18-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah80140-il | 50,000 | 9 | 5.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80140-il | 50,000 | 5 | 14.3 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80140-il | 100,000 | 9 | 22.5 at α=14° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80140-il | 100,000 | 5 | 35.7 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80140-il | 200,000 | 9 | 70.9 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80140-il | 200,000 | 5 | 74.2 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80140-il | 500,000 | 9 | 116.4 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80140-il | 500,000 | 5 | 113.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah80140-il | 1,000,000 | 9 | 149.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah80140-il | 1,000,000 | 5 | 139 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag14-il | 50,000 | 9 | 34.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag14-il | 50,000 | 5 | 35.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag14-il | 100,000 | 9 | 48.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag14-il | 100,000 | 5 | 47.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag14-il | 200,000 | 9 | 62.2 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag14-il | 200,000 | 5 | 59.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag14-il | 500,000 | 9 | 80.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag14-il | 500,000 | 5 | 76 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag14-il | 1,000,000 | 9 | 93.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag14-il | 1,000,000 | 5 | 89.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e186-il | 50,000 | 9 | 29.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e186-il | 50,000 | 5 | 31.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e186-il | 100,000 | 9 | 46 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e186-il | 100,000 | 5 | 45.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e186-il | 200,000 | 9 | 61.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e186-il | 200,000 | 5 | 58.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e186-il | 500,000 | 9 | 79.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e186-il | 500,000 | 5 | 71.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e186-il | 1,000,000 | 9 | 90.7 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e186-il | 1,000,000 | 5 | 73.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag12-il | 50,000 | 9 | 33.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag12-il | 50,000 | 5 | 35.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag12-il | 100,000 | 9 | 47.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag12-il | 100,000 | 5 | 47 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag12-il | 200,000 | 9 | 61.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag12-il | 200,000 | 5 | 58.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag12-il | 500,000 | 9 | 79.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag12-il | 500,000 | 5 | 74.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag12-il | 1,000,000 | 9 | 92.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag12-il | 1,000,000 | 5 | 87.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah21-9-il | 50,000 | 9 | 34.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-9-il | 50,000 | 5 | 34.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah21-9-il | 100,000 | 9 | 51.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-9-il | 100,000 | 5 | 49 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah21-9-il | 200,000 | 9 | 73.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-9-il | 200,000 | 5 | 65 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah21-9-il | 500,000 | 9 | 103.2 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-9-il | 500,000 | 5 | 78.4 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah21-9-il | 1,000,000 | 9 | 113.5 at α=1.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah21-9-il | 1,000,000 | 5 | 79.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag18-il | 50,000 | 9 | 35.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag18-il | 50,000 | 5 | 36.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag18-il | 100,000 | 9 | 50.8 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag18-il | 100,000 | 5 | 48.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag18-il | 200,000 | 9 | 65.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag18-il | 200,000 | 5 | 60.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag18-il | 500,000 | 9 | 81.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag18-il | 500,000 | 5 | 77 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag18-il | 1,000,000 | 9 | 95.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag18-il | 1,000,000 | 5 | 90.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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