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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(sd7043-il) SD7043 (9.1%) | Selig/Donovan SD7043 low Reynolds number airfoil Max thickness 9.1% at 26.6% chord Max camber 3.3% at 50.2% chord | Remove Airfoil details Airfoil plotter |
(mh78-il) MH 78 14.47% | Martin Hepperle MH 78 for flying wings (hang glider) Max thickness 14.4% at 22.1% chord Max camber 1.9% at 17.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (sd7043-il,mh78-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| sd7043-il | 50,000 | 9 | 38.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7043-il | 50,000 | 5 | 41.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7043-il | 100,000 | 9 | 60.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7043-il | 100,000 | 5 | 59.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7043-il | 200,000 | 9 | 82.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7043-il | 200,000 | 5 | 76 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7043-il | 500,000 | 9 | 110.1 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7043-il | 500,000 | 5 | 94.2 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| sd7043-il | 1,000,000 | 9 | 126.7 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| sd7043-il | 1,000,000 | 5 | 105.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh78-il | 50,000 | 9 | 9.9 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh78-il | 50,000 | 5 | 18.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh78-il | 100,000 | 9 | 22.4 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh78-il | 100,000 | 5 | 33.6 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh78-il | 200,000 | 9 | 42.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh78-il | 200,000 | 5 | 51.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh78-il | 500,000 | 9 | 73.6 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh78-il | 500,000 | 5 | 77.3 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh78-il | 1,000,000 | 9 | 99.2 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh78-il | 1,000,000 | 5 | 97.2 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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