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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(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 |
(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 |
(goe228-il) GOE 228 (MVA H.38) AIRFOIL | Gottingen 228 (MVA H.38) airfoil Max thickness 17.9% at 29.4% chord Max camber 7% at 49.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe176-il,goe09k-il,goe228-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| 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 | |
| goe228-il | 50,000 | 9 | 5.6 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe228-il | 50,000 | 5 | 25.9 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe228-il | 100,000 | 9 | 45.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe228-il | 100,000 | 5 | 51.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe228-il | 200,000 | 9 | 70.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe228-il | 200,000 | 5 | 66.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe228-il | 500,000 | 9 | 92.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe228-il | 500,000 | 5 | 88.2 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe228-il | 1,000,000 | 9 | 116.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe228-il | 1,000,000 | 5 | 109 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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