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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(ah94145-il) AH 94-145 | Althaus AH 94-145 airfoil Max thickness 14.6% at 38.9% chord Max camber 5.6% at 44.6% chord | Remove Airfoil details Airfoil plotter |
(goe415-il) GOE 415 AIRFOIL | Gottingen 415 airfoil Max thickness 8.5% at 19.9% chord Max camber 3.7% at 29.9% chord | Remove Airfoil details Airfoil plotter |
(goe591-il) GOE 591 AIRFOIL | Gottingen 591 airfoil Max thickness 11.2% at 30% chord Max camber 5.1% at 40% chord | Remove Airfoil details Airfoil plotter |
(rc510-il) NASA RC(5)-10 AIRFOIL | NASA/Langley RC(5)-10 rotorcraft airfoil Max thickness 10% at 40.1% chord Max camber 2.2% at 25.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ah94145-il,goe415-il,goe591-il,rc510-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah94145-il | 50,000 | 9 | 6.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah94145-il | 50,000 | 5 | 14.8 at α=13.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah94145-il | 100,000 | 9 | 28 at α=12.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah94145-il | 100,000 | 5 | 30.6 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah94145-il | 200,000 | 9 | 75.7 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah94145-il | 200,000 | 5 | 81.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah94145-il | 500,000 | 9 | 135.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah94145-il | 500,000 | 5 | 132.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah94145-il | 1,000,000 | 9 | 177.4 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah94145-il | 1,000,000 | 5 | 164.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe415-il | 50,000 | 9 | 34 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe415-il | 50,000 | 5 | 37.2 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe415-il | 100,000 | 9 | 52 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe415-il | 100,000 | 5 | 53.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe415-il | 200,000 | 9 | 68.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe415-il | 200,000 | 5 | 69.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe415-il | 500,000 | 9 | 92.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe415-il | 500,000 | 5 | 90.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe415-il | 1,000,000 | 9 | 109.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe415-il | 1,000,000 | 5 | 106.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe591-il | 50,000 | 9 | 16 at α=14.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe591-il | 50,000 | 5 | 34.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe591-il | 100,000 | 9 | 52.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe591-il | 100,000 | 5 | 57.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe591-il | 200,000 | 9 | 77.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe591-il | 200,000 | 5 | 76.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe591-il | 500,000 | 9 | 108 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe591-il | 500,000 | 5 | 103.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe591-il | 1,000,000 | 9 | 132.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe591-il | 1,000,000 | 5 | 122.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc510-il | 50,000 | 9 | 31.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc510-il | 50,000 | 5 | 32.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc510-il | 100,000 | 9 | 46.6 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc510-il | 100,000 | 5 | 43.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc510-il | 200,000 | 9 | 60.8 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc510-il | 200,000 | 5 | 54.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc510-il | 500,000 | 9 | 76.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc510-il | 500,000 | 5 | 75.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc510-il | 1,000,000 | 9 | 94.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc510-il | 1,000,000 | 5 | 92.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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