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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(goe413-il) GOE 413 AIRFOIL | Gottingen 413 airfoil Max thickness 16.4% at 30% chord Max camber 4.6% at 40% chord | Remove Airfoil details Airfoil plotter |
(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 |
(giiig-il) GIII BL167 AIRFOIL | Grumman/Gulfstream GIII transonic airfoils Max thickness 8.3% at 44.9% chord Max camber 1.3% at 29.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe413-il,goe619-il,giiig-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe413-il | 50,000 | 9 | 7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe413-il | 50,000 | 5 | 23.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe413-il | 100,000 | 9 | 47.3 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe413-il | 100,000 | 5 | 52.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe413-il | 200,000 | 9 | 75.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe413-il | 200,000 | 5 | 74.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe413-il | 500,000 | 9 | 108.3 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe413-il | 500,000 | 5 | 98.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe413-il | 1,000,000 | 9 | 130.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe413-il | 1,000,000 | 5 | 107.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
| giiig-il | 50,000 | 9 | 31.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiig-il | 50,000 | 5 | 32.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiig-il | 100,000 | 9 | 46.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiig-il | 100,000 | 5 | 44.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiig-il | 200,000 | 9 | 65.9 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiig-il | 200,000 | 5 | 56.1 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiig-il | 500,000 | 9 | 78.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiig-il | 500,000 | 5 | 62.1 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| giiig-il | 1,000,000 | 9 | 83 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| giiig-il | 1,000,000 | 5 | 73 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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