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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(ma409-il) MA409 (original) (modified line 7) | Michael Achterberg MA409 F1C class free flight airfoil (original) Max thickness 6.8% at 25% chord Max camber 3.3% at 50% chord | Remove Airfoil details Airfoil plotter |
(rhodesg32-il) Rhode St. Genese 32 | Rhode St. Genese 32 airfoil Max thickness 11.9% at 30% chord Max camber 3.9% at 40% chord | Remove Airfoil details Airfoil plotter |
(e325-il) EPPLER 325 AIRFOIL | Eppler E325 flying wing airfoil Max thickness 12.6% at 34.3% chord Max camber 1.8% at 16.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ma409-il,rhodesg32-il,e325-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ma409-il | 50,000 | 9 | 42.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ma409-il | 50,000 | 5 | 42.5 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ma409-il | 100,000 | 9 | 61.9 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ma409-il | 100,000 | 5 | 59.6 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ma409-il | 200,000 | 9 | 81.5 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ma409-il | 200,000 | 5 | 72.8 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ma409-il | 500,000 | 9 | 99.3 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ma409-il | 500,000 | 5 | 89.3 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ma409-il | 1,000,000 | 9 | 110.6 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ma409-il | 1,000,000 | 5 | 94.8 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rhodesg32-il | 50,000 | 9 | 24.3 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rhodesg32-il | 50,000 | 5 | 33.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rhodesg32-il | 100,000 | 9 | 45.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rhodesg32-il | 100,000 | 5 | 48.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rhodesg32-il | 200,000 | 9 | 64.3 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rhodesg32-il | 200,000 | 5 | 64.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rhodesg32-il | 500,000 | 9 | 92.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rhodesg32-il | 500,000 | 5 | 89.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rhodesg32-il | 1,000,000 | 9 | 115 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rhodesg32-il | 1,000,000 | 5 | 108 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e325-il | 50,000 | 9 | 17.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e325-il | 50,000 | 5 | 26.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e325-il | 100,000 | 9 | 39.2 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e325-il | 100,000 | 5 | 42.6 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e325-il | 200,000 | 9 | 58.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e325-il | 200,000 | 5 | 51.1 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e325-il | 500,000 | 9 | 69.6 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e325-il | 500,000 | 5 | 69.2 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e325-il | 1,000,000 | 9 | 88.2 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e325-il | 1,000,000 | 5 | 82.6 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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