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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(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 |
(goe57-il) GOE 57 AIRFOIL | Gottingen 57 airfoil Max thickness 6.3% at 19.9% chord Max camber 5.1% at 39.9% chord | Remove Airfoil details Airfoil plotter |
(goe548-il) GOE 548 AIRFOIL | Gottingen 548 airfoil Max thickness 11.9% at 40% chord Max camber 2.3% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx69h083-il,goe57-il,goe548-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| goe57-il | 50,000 | 9 | 41.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe57-il | 50,000 | 5 | 43.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe57-il | 100,000 | 9 | 63.3 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe57-il | 100,000 | 5 | 59.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe57-il | 200,000 | 9 | 82.4 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe57-il | 200,000 | 5 | 70.2 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe57-il | 500,000 | 9 | 93 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe57-il | 500,000 | 5 | 86.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe57-il | 1,000,000 | 9 | 105.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe57-il | 1,000,000 | 5 | 102.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe548-il | 50,000 | 9 | 34.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe548-il | 50,000 | 5 | 32.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe548-il | 100,000 | 9 | 53.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe548-il | 100,000 | 5 | 51.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe548-il | 200,000 | 9 | 74.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe548-il | 200,000 | 5 | 68.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe548-il | 500,000 | 9 | 95 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe548-il | 500,000 | 5 | 76.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe548-il | 1,000,000 | 9 | 100.7 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe548-il | 1,000,000 | 5 | 76.3 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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