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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(goe421-il) GOE 421 AIRFOIL | Gottingen 421 airfoil Max thickness 19% at 29.3% chord Max camber 8.1% at 49.3% chord | Remove Airfoil details Airfoil plotter |
(goe408-il) GOE 408 AIRFOIL | Gottingen 408 airfoil Max thickness 7.8% at 30% chord Max camber 4.1% at 30% chord | Remove Airfoil details Airfoil plotter |
(goe335-il) GOE 335 (D.F.W.) AIRFOIL | Gottingen 335 (D.F.W.) airfoil Max thickness 6.9% at 20% chord Max camber 4.8% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe176-il) GOE 176 (ALBATROS 7020) AIRFOIL | Gottingen 176 (Albatros 7020) airfoil Max thickness 10.3% at 19.8% chord Max camber 5.6% at 39.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe421-il,goe408-il,goe335-il,goe176-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe421-il | 50,000 | 9 | 4.4 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe421-il | 50,000 | 5 | 11.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe421-il | 100,000 | 9 | 31.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe421-il | 100,000 | 5 | 34.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe421-il | 200,000 | 9 | 68.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe421-il | 200,000 | 5 | 60.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe421-il | 500,000 | 9 | 96.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe421-il | 500,000 | 5 | 76.6 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe421-il | 1,000,000 | 9 | 103.9 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe421-il | 1,000,000 | 5 | 86.2 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe408-il | 50,000 | 9 | 35.8 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe408-il | 50,000 | 5 | 40.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe408-il | 100,000 | 9 | 58.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe408-il | 100,000 | 5 | 59.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe408-il | 200,000 | 9 | 78.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe408-il | 200,000 | 5 | 75.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe408-il | 500,000 | 9 | 101.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe408-il | 500,000 | 5 | 94.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe408-il | 1,000,000 | 9 | 119.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe408-il | 1,000,000 | 5 | 102.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe335-il | 50,000 | 9 | 38.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe335-il | 50,000 | 5 | 41.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe335-il | 100,000 | 9 | 56.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe335-il | 100,000 | 5 | 57.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe335-il | 200,000 | 9 | 75.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe335-il | 200,000 | 5 | 75.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe335-il | 500,000 | 9 | 102.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe335-il | 500,000 | 5 | 100.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe335-il | 1,000,000 | 9 | 123.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe335-il | 1,000,000 | 5 | 119.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe176-il | 50,000 | 9 | 30.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe176-il | 50,000 | 5 | 40.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe176-il | 100,000 | 9 | 56 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe176-il | 100,000 | 5 | 57.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe176-il | 200,000 | 9 | 73.7 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe176-il | 200,000 | 5 | 73.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe176-il | 500,000 | 9 | 99.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe176-il | 500,000 | 5 | 87 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe176-il | 1,000,000 | 9 | 113.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe176-il | 1,000,000 | 5 | 93.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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