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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(mh45-il) MH 45 9.85% | Martin Hepperle MH 45 for flying wings Max thickness 9.8% at 26.9% chord Max camber 1.7% at 36.6% chord | Remove Airfoil details Airfoil plotter |
(goe439-il) GOE 439 AIRFOIL | Gottingen 439 airfoil Max thickness 7.9% at 30% chord Max camber 5.2% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe342-il) GOE 342 AIRFOIL | Gottingen 342 airfoil Max thickness 5.4% at 20% chord Max camber 6.2% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (mh45-il,goe439-il,goe342-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| mh45-il | 50,000 | 9 | 27.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh45-il | 50,000 | 5 | 32.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh45-il | 100,000 | 9 | 44.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh45-il | 100,000 | 5 | 45.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh45-il | 200,000 | 9 | 60.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh45-il | 200,000 | 5 | 58.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh45-il | 500,000 | 9 | 81.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh45-il | 500,000 | 5 | 75.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh45-il | 1,000,000 | 9 | 95.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh45-il | 1,000,000 | 5 | 88.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe439-il | 50,000 | 9 | 28.7 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe439-il | 50,000 | 5 | 40.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe439-il | 100,000 | 9 | 59.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe439-il | 100,000 | 5 | 61.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe439-il | 200,000 | 9 | 79.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe439-il | 200,000 | 5 | 80.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe439-il | 500,000 | 9 | 108.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe439-il | 500,000 | 5 | 106.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe439-il | 1,000,000 | 9 | 129.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe439-il | 1,000,000 | 5 | 123.7 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe342-il | 50,000 | 9 | 44.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe342-il | 50,000 | 5 | 47.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe342-il | 100,000 | 9 | 71.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe342-il | 100,000 | 5 | 71.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe342-il | 200,000 | 9 | 99.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe342-il | 200,000 | 5 | 85.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe342-il | 500,000 | 9 | 109.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe342-il | 500,000 | 5 | 105.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe342-il | 1,000,000 | 9 | 130.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe342-il | 1,000,000 | 5 | 111.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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