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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(goe09k-il) GOE 9K AIRFOIL | Gottingen 9K airfoil Max thickness 2.5% at 50% chord Max camber 0.9% at 60% chord | Remove Airfoil details Airfoil plotter |
(ag45ct02r-il) AG45ct -02f | Drela AG45ct -02f airfoil Max thickness 6.9% at 23.3% chord Max camber 1.8% at 33.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe09k-il,ag45ct02r-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe09k-il | 50,000 | 9 | 20.1 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe09k-il | 50,000 | 5 | 18.7 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe09k-il | 100,000 | 9 | 23.8 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe09k-il | 100,000 | 5 | 23.8 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe09k-il | 200,000 | 9 | 29.3 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe09k-il | 200,000 | 5 | 29.1 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe09k-il | 500,000 | 9 | 79.4 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe09k-il | 500,000 | 5 | 60.5 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe09k-il | 1,000,000 | 9 | 77.7 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe09k-il | 1,000,000 | 5 | 63.4 at α=0.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag45ct02r-il | 50,000 | 9 | 30.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag45ct02r-il | 50,000 | 5 | 34.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag45ct02r-il | 100,000 | 9 | 45.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag45ct02r-il | 100,000 | 5 | 46.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag45ct02r-il | 200,000 | 9 | 60.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag45ct02r-il | 200,000 | 5 | 59.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag45ct02r-il | 500,000 | 9 | 80.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag45ct02r-il | 500,000 | 5 | 76.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag45ct02r-il | 1,000,000 | 9 | 94.6 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag45ct02r-il | 1,000,000 | 5 | 89.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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