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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(goe328-il) GOE 328 AIRFOIL | Gottingen 328 airfoil Max thickness 8.2% at 30% chord Max camber 4.3% at 30% chord | Remove Airfoil details Airfoil plotter |
(daytonwright6-il) Dayton-Wright 6 | Dayton-Wright 6 airfoil Max thickness 13.6% at 30% chord Max camber 4.9% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe173-il) GOE 173 (ALBATROS 6020) AIRFOIL | Gottingen 173 (Albatros 6020) airfoil Max thickness 7.8% at 20% chord Max camber 5.9% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe703-il) GOE 703 AIRFOIL | Gottingen 703 airfoil Max thickness 19.4% at 30% chord Max camber 2.3% at 30% chord | Remove Airfoil details Airfoil plotter |
(goe420-il) GOE 420 AIRFOIL | Gottingen 420 airfoil Max thickness 18.8% at 30% chord Max camber 4.3% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe328-il,daytonwright6-il,goe173-il,goe703-il,goe420-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe328-il | 50,000 | 9 | 36.1 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe328-il | 50,000 | 5 | 39.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe328-il | 100,000 | 9 | 56.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe328-il | 100,000 | 5 | 57.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe328-il | 200,000 | 9 | 75.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe328-il | 200,000 | 5 | 74.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe328-il | 500,000 | 9 | 101.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe328-il | 500,000 | 5 | 96.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe328-il | 1,000,000 | 9 | 120.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe328-il | 1,000,000 | 5 | 111.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| daytonwright6-il | 50,000 | 9 | 11 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| daytonwright6-il | 50,000 | 5 | 31.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| daytonwright6-il | 100,000 | 9 | 45.6 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| daytonwright6-il | 100,000 | 5 | 49.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| daytonwright6-il | 200,000 | 9 | 66.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| daytonwright6-il | 200,000 | 5 | 66.4 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| daytonwright6-il | 500,000 | 9 | 92.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| daytonwright6-il | 500,000 | 5 | 89.6 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| daytonwright6-il | 1,000,000 | 9 | 115.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| daytonwright6-il | 1,000,000 | 5 | 111.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe173-il | 50,000 | 9 | 33.1 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe173-il | 50,000 | 5 | 42.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe173-il | 100,000 | 9 | 56.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe173-il | 100,000 | 5 | 60.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe173-il | 200,000 | 9 | 77.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe173-il | 200,000 | 5 | 75.7 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe173-il | 500,000 | 9 | 101.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe173-il | 500,000 | 5 | 101.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe173-il | 1,000,000 | 9 | 124.6 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe173-il | 1,000,000 | 5 | 122.3 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe703-il | 50,000 | 9 | 5.5 at α=0.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe703-il | 50,000 | 5 | 22.3 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe703-il | 100,000 | 9 | 40 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe703-il | 100,000 | 5 | 43 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe703-il | 200,000 | 9 | 63.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe703-il | 200,000 | 5 | 49.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe703-il | 500,000 | 9 | 67 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe703-il | 500,000 | 5 | 57.4 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe703-il | 1,000,000 | 9 | 75.5 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe703-il | 1,000,000 | 5 | 65.6 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe420-il | 50,000 | 9 | 4 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe420-il | 50,000 | 5 | 13.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe420-il | 100,000 | 9 | 32.7 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe420-il | 100,000 | 5 | 44.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe420-il | 200,000 | 9 | 66.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe420-il | 200,000 | 5 | 62.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe420-il | 500,000 | 9 | 89.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe420-il | 500,000 | 5 | 83.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe420-il | 1,000,000 | 9 | 111.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe420-il | 1,000,000 | 5 | 102.2 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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