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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(goe199-il) GOE 199 (L.F.G. 5406) AIRFOIL | Gottingen 199 (L.F.G. 5406) airfoil Max thickness 7.3% at 30% chord Max camber 5.2% at 30% chord | Remove Airfoil details Airfoil plotter |
(raf33-il) RAF 33 AIRFOIL | RAF-33 airfoil Max thickness 12.6% at 30% chord Max camber 4.7% at 30% chord | Remove Airfoil details Airfoil plotter |
(e222-il) E222 (10.17%) | Eppler E222 low Reynolds number airfoil Max thickness 10.2% at 31.1% chord Max camber 2.1% at 55.3% chord | Remove Airfoil details Airfoil plotter |
(goe314-il) GOE 314 (HANSA-BRANDENBURG) AIRFOIL | Gottingen 314 (Hansa-Brandenburg) airfoil Max thickness 8% at 29.9% chord Max camber 4.7% at 29.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe199-il,raf33-il,e222-il,goe314-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe199-il | 50,000 | 9 | 36.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe199-il | 50,000 | 5 | 40.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe199-il | 100,000 | 9 | 55.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe199-il | 100,000 | 5 | 54.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe199-il | 200,000 | 9 | 72 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe199-il | 200,000 | 5 | 67.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe199-il | 500,000 | 9 | 89.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe199-il | 500,000 | 5 | 89.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe199-il | 1,000,000 | 9 | 108.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe199-il | 1,000,000 | 5 | 106.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf33-il | 50,000 | 9 | 6.6 at α=-5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf33-il | 50,000 | 5 | 19.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf33-il | 100,000 | 9 | 39 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf33-il | 100,000 | 5 | 48.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf33-il | 200,000 | 9 | 71.8 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf33-il | 200,000 | 5 | 73.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf33-il | 500,000 | 9 | 107.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf33-il | 500,000 | 5 | 99.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| raf33-il | 1,000,000 | 9 | 127.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| raf33-il | 1,000,000 | 5 | 110.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e222-il | 50,000 | 9 | 36.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e222-il | 50,000 | 5 | 38.8 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e222-il | 100,000 | 9 | 56.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e222-il | 100,000 | 5 | 55.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e222-il | 200,000 | 9 | 76.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e222-il | 200,000 | 5 | 71.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e222-il | 500,000 | 9 | 101.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e222-il | 500,000 | 5 | 89.8 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e222-il | 1,000,000 | 9 | 118.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e222-il | 1,000,000 | 5 | 99.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe314-il | 50,000 | 9 | 28.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe314-il | 50,000 | 5 | 36.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe314-il | 100,000 | 9 | 48.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe314-il | 100,000 | 5 | 54.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe314-il | 200,000 | 9 | 70.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe314-il | 200,000 | 5 | 71.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe314-il | 500,000 | 9 | 98.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe314-il | 500,000 | 5 | 91 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe314-il | 1,000,000 | 9 | 117.1 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe314-il | 1,000,000 | 5 | 104.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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