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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(goe371-il) GOE 371 AIRFOIL | Gottingen 371 airfoil Max thickness 7% at 29.9% chord Max camber 4.6% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(mh92-il) MH 92 15.49% | Martin Hepperle MH 92 parafoil Max thickness 15.5% at 27.4% chord Max camber 1.4% at 15.1% chord | Remove Airfoil details Airfoil plotter |
(mb253515sm-il) MB253515 15.0% smoothed | Mike Bame MB253515 low Reynolds number airfoil Max thickness 15% at 35% chord Max camber 2.5% at 37.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe371-il,mh92-il,mb253515sm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe371-il | 50,000 | 9 | 37.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe371-il | 50,000 | 5 | 43.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe371-il | 100,000 | 9 | 61.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe371-il | 100,000 | 5 | 62.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe371-il | 200,000 | 9 | 82 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe371-il | 200,000 | 5 | 80 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe371-il | 500,000 | 9 | 108.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe371-il | 500,000 | 5 | 103.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe371-il | 1,000,000 | 9 | 129.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe371-il | 1,000,000 | 5 | 120.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh92-il | 50,000 | 9 | 15.4 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh92-il | 50,000 | 5 | 24.9 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh92-il | 100,000 | 9 | 33.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh92-il | 100,000 | 5 | 40 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh92-il | 200,000 | 9 | 52.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh92-il | 200,000 | 5 | 54.7 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh92-il | 500,000 | 9 | 76.6 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh92-il | 500,000 | 5 | 73.4 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mh92-il | 1,000,000 | 9 | 94.2 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mh92-il | 1,000,000 | 5 | 90.1 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mb253515sm-il | 50,000 | 9 | 7.5 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mb253515sm-il | 50,000 | 5 | 25.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mb253515sm-il | 100,000 | 9 | 48.5 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mb253515sm-il | 100,000 | 5 | 49 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mb253515sm-il | 200,000 | 9 | 70 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mb253515sm-il | 200,000 | 5 | 68.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mb253515sm-il | 500,000 | 9 | 92.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mb253515sm-il | 500,000 | 5 | 83.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| mb253515sm-il | 1,000,000 | 9 | 105.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| mb253515sm-il | 1,000,000 | 5 | 96.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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