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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(goe278-il) GOE 278 (DAIMLER IX) AIRFOIL | Gottingen 278 (DAIMLER IX) airfoil Max thickness 7.4% at 29.9% chord Max camber 4.3% at 29.9% chord | Remove Airfoil details Airfoil plotter |
(goe142-il) GOE 142 (MVA H.19) AIRFOIL | Gottingen 142 (MVA H.19) airfoil Max thickness 6.2% at 24.9% chord Max camber 3.8% at 34.9% chord | Remove Airfoil details Airfoil plotter |
(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 |
(ah93156-il) AH 93-156 | Althaus AH 93-156 airfoil Max thickness 15.7% at 39.5% chord Max camber 3.7% at 41.5% chord | Remove Airfoil details Airfoil plotter |
(goe308-il) GOE 308 (MVA H.40) AIRFOIL | Gottingen 308 (MVA H.40) airfoil Max thickness 8.1% at 29.9% chord Max camber 5% at 29.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe278-il,goe142-il,ah80140-il,ah93156-il,goe308-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe278-il | 50,000 | 9 | 38.5 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe278-il | 50,000 | 5 | 40.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe278-il | 100,000 | 9 | 55.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe278-il | 100,000 | 5 | 56.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe278-il | 200,000 | 9 | 72.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe278-il | 200,000 | 5 | 72.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe278-il | 500,000 | 9 | 95.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe278-il | 500,000 | 5 | 92.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe278-il | 1,000,000 | 9 | 113.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe278-il | 1,000,000 | 5 | 102.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe142-il | 50,000 | 9 | 36.1 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe142-il | 50,000 | 5 | 41 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe142-il | 100,000 | 9 | 55.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe142-il | 100,000 | 5 | 56.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe142-il | 200,000 | 9 | 74.2 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe142-il | 200,000 | 5 | 72.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe142-il | 500,000 | 9 | 99 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe142-il | 500,000 | 5 | 94.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe142-il | 1,000,000 | 9 | 118.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe142-il | 1,000,000 | 5 | 111.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
| ah93156-il | 50,000 | 9 | 4.8 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93156-il | 50,000 | 5 | 15.6 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93156-il | 100,000 | 9 | 39 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93156-il | 100,000 | 5 | 35.5 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93156-il | 200,000 | 9 | 72.1 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93156-il | 200,000 | 5 | 64.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93156-il | 500,000 | 9 | 103.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93156-il | 500,000 | 5 | 94.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93156-il | 1,000,000 | 9 | 125 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93156-il | 1,000,000 | 5 | 114.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe308-il | 50,000 | 9 | 32.2 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe308-il | 50,000 | 5 | 37.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe308-il | 100,000 | 9 | 54.3 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe308-il | 100,000 | 5 | 55.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe308-il | 200,000 | 9 | 74.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe308-il | 200,000 | 5 | 74.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe308-il | 500,000 | 9 | 103 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe308-il | 500,000 | 5 | 100.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe308-il | 1,000,000 | 9 | 126.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe308-il | 1,000,000 | 5 | 115.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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