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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(goe746-il) GOE 746 AIRFOIL | Gottingen 746 airfoil Max thickness 9.8% at 30% chord Max camber 5% at 30% chord | Remove Airfoil details Airfoil plotter |
(goe155-il) GOE 155 (SSW D.1) AIRFOIL | Gottingen 155 (SSW D.1) airfoil Max thickness 7% at 29.9% chord Max camber 5.3% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(e423-il) E423 | Eppler E423 high lift airfoil Max thickness 12.5% at 23.7% chord Max camber 9.5% at 41.4% chord | Remove Airfoil details Airfoil plotter |
(mh121-il) MH 121 8.76% | Martin Hepperle MH 121 for tip section of a propeller Max thickness 8.8% at 37.9% chord Max camber 3% at 62.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe746-il,goe155-il,e423-il,mh121-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe746-il | 50,000 | 9 | 7.9 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe746-il | 50,000 | 5 | 20.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe746-il | 100,000 | 9 | 46.3 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe746-il | 100,000 | 5 | 49.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe746-il | 200,000 | 9 | 73.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe746-il | 200,000 | 5 | 73.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe746-il | 500,000 | 9 | 106.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe746-il | 500,000 | 5 | 102.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe746-il | 1,000,000 | 9 | 129.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe746-il | 1,000,000 | 5 | 118.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe155-il | 50,000 | 9 | 40.1 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe155-il | 50,000 | 5 | 42.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe155-il | 100,000 | 9 | 59.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe155-il | 100,000 | 5 | 61.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe155-il | 200,000 | 9 | 82.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe155-il | 200,000 | 5 | 78.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe155-il | 500,000 | 9 | 107.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe155-il | 500,000 | 5 | 98.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe155-il | 1,000,000 | 9 | 123.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe155-il | 1,000,000 | 5 | 111 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e423-il | 50,000 | 9 | 6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e423-il | 50,000 | 5 | 13.9 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e423-il | 100,000 | 9 | 12.5 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e423-il | 100,000 | 5 | 51.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e423-il | 200,000 | 9 | 73.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e423-il | 200,000 | 5 | 84.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e423-il | 500,000 | 9 | 123.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e423-il | 500,000 | 5 | 120.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e423-il | 1,000,000 | 9 | 156.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e423-il | 1,000,000 | 5 | 145.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh121-il | 50,000 | 9 | 31.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh121-il | 50,000 | 5 | 35.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh121-il | 100,000 | 9 | 53.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh121-il | 100,000 | 5 | 57.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh121-il | 200,000 | 9 | 84 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh121-il | 200,000 | 5 | 82.4 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh121-il | 500,000 | 9 | 125.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh121-il | 500,000 | 5 | 107.8 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh121-il | 1,000,000 | 9 | 139.1 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh121-il | 1,000,000 | 5 | 117.7 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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