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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(goe619-il) GOE 619 AIRFOIL | Gottingen 619 airfoil Max thickness 13.7% at 19.5% chord Max camber 4.5% at 49.5% chord | Remove Airfoil details Airfoil plotter |
(goe596-il) GOE 596 AIRFOIL | Gottingen 596 airfoil Max thickness 9.8% at 30% chord Max camber 4% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe547-il) GOE 547 AIRFOIL | Gottingen 547 airfoil Max thickness 10.5% at 29.7% chord Max camber 4% at 49.7% chord | Remove Airfoil details Airfoil plotter |
(goe622-il) GOE 622 AIRFOIL | Gottingen 622 airfoil Max thickness 8% at 30% chord Max camber 2.4% at 40% chord | Remove Airfoil details Airfoil plotter |
(fx69h098-il) BELL/WORTMANN FX 69-H-098 AIRFOIL | Bell/Wortmann FX 69-H-098 rotorcraft airfoil Max thickness 9.9% at 28.2% chord Max camber 1.7% at 22.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe619-il,goe596-il,goe547-il,goe622-il,fx69h098-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe619-il | 50,000 | 9 | 22 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe619-il | 50,000 | 5 | 33.3 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe619-il | 100,000 | 9 | 52.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe619-il | 100,000 | 5 | 51.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe619-il | 200,000 | 9 | 73.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe619-il | 200,000 | 5 | 67.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe619-il | 500,000 | 9 | 99.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe619-il | 500,000 | 5 | 82 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe619-il | 1,000,000 | 9 | 108.9 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe619-il | 1,000,000 | 5 | 99.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe596-il | 50,000 | 9 | 35.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe596-il | 50,000 | 5 | 37 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe596-il | 100,000 | 9 | 56.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe596-il | 100,000 | 5 | 57.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe596-il | 200,000 | 9 | 77.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe596-il | 200,000 | 5 | 75.6 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe596-il | 500,000 | 9 | 105.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe596-il | 500,000 | 5 | 97.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe596-il | 1,000,000 | 9 | 125.7 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe596-il | 1,000,000 | 5 | 112.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe547-il | 50,000 | 9 | 36.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe547-il | 50,000 | 5 | 35.2 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe547-il | 100,000 | 9 | 60.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe547-il | 100,000 | 5 | 59.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe547-il | 200,000 | 9 | 86.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe547-il | 200,000 | 5 | 82.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe547-il | 500,000 | 9 | 120.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe547-il | 500,000 | 5 | 105.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe547-il | 1,000,000 | 9 | 143.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe547-il | 1,000,000 | 5 | 104.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe622-il | 50,000 | 9 | 35.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe622-il | 50,000 | 5 | 38.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe622-il | 100,000 | 9 | 53.2 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe622-il | 100,000 | 5 | 52.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe622-il | 200,000 | 9 | 69.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe622-il | 200,000 | 5 | 64.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe622-il | 500,000 | 9 | 88.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe622-il | 500,000 | 5 | 75.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe622-il | 1,000,000 | 9 | 98.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe622-il | 1,000,000 | 5 | 82 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx69h098-il | 50,000 | 9 | 27.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69h098-il | 50,000 | 5 | 31.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx69h098-il | 100,000 | 9 | 43.7 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69h098-il | 100,000 | 5 | 45.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx69h098-il | 200,000 | 9 | 59.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69h098-il | 200,000 | 5 | 59.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx69h098-il | 500,000 | 9 | 81.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69h098-il | 500,000 | 5 | 79 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx69h098-il | 1,000,000 | 9 | 98.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69h098-il | 1,000,000 | 5 | 93.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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