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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(goe617-il) GOE 617 AIRFOIL | Gottingen 617 airfoil Max thickness 13.9% at 30% chord Max camber 2.2% at 30% chord | Remove Airfoil details Airfoil plotter |
(fx69h083-il) BELL/WORTMANN FX 69-H-083 AIRFOIL | Bell/Wortmann FX 69-H-083 rotorcraft airfoil Max thickness 8.4% at 33.3% chord Max camber 2.5% at 33.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (goe617-il,fx69h083-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| goe617-il | 50,000 | 9 | 29.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe617-il | 50,000 | 5 | 31.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe617-il | 100,000 | 9 | 49.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe617-il | 100,000 | 5 | 48.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe617-il | 200,000 | 9 | 67.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe617-il | 200,000 | 5 | 63 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe617-il | 500,000 | 9 | 87.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe617-il | 500,000 | 5 | 72.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe617-il | 1,000,000 | 9 | 91 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe617-il | 1,000,000 | 5 | 82.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx69h083-il | 50,000 | 9 | 36.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69h083-il | 50,000 | 5 | 37 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx69h083-il | 100,000 | 9 | 53 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69h083-il | 100,000 | 5 | 52.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx69h083-il | 200,000 | 9 | 69.7 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69h083-il | 200,000 | 5 | 66.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx69h083-il | 500,000 | 9 | 90.1 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69h083-il | 500,000 | 5 | 78.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx69h083-il | 1,000,000 | 9 | 101 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx69h083-il | 1,000,000 | 5 | 81.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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