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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(e64-il) E64 (8.45%) | Eppler E64 low Reynolds number airfoil Max thickness 8.4% at 27.8% chord Max camber 2.9% at 56.5% chord | Remove Airfoil details Airfoil plotter |
(goe29b-il) GOE 29B AIRFOIL | Gottingen 29B airfoil Max thickness 9.4% at 19.8% chord Max camber 6.5% at 29.8% chord | Remove Airfoil details Airfoil plotter |
(ls417-il) NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL | NASA/Langley/Whitcomb LS(1)-0417 (GA(W)-1) general aviation airfoil Max thickness 17% at 40% chord Max camber 2.4% at 65% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e64-il,goe29b-il,ls417-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e64-il | 50,000 | 9 | 41.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e64-il | 50,000 | 5 | 42.5 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e64-il | 100,000 | 9 | 64 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e64-il | 100,000 | 5 | 62.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e64-il | 200,000 | 9 | 88.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e64-il | 200,000 | 5 | 81.8 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e64-il | 500,000 | 9 | 120.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e64-il | 500,000 | 5 | 103.3 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e64-il | 1,000,000 | 9 | 140.7 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e64-il | 1,000,000 | 5 | 113.2 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe29b-il | 50,000 | 9 | 22.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe29b-il | 50,000 | 5 | 37.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe29b-il | 100,000 | 9 | 52.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe29b-il | 100,000 | 5 | 57.8 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe29b-il | 200,000 | 9 | 77.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe29b-il | 200,000 | 5 | 75 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe29b-il | 500,000 | 9 | 99.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe29b-il | 500,000 | 5 | 94.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe29b-il | 1,000,000 | 9 | 118.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe29b-il | 1,000,000 | 5 | 116.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls417-il | 50,000 | 9 | 29.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls417-il | 50,000 | 5 | 25 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls417-il | 100,000 | 9 | 42.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls417-il | 100,000 | 5 | 41 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls417-il | 200,000 | 9 | 61 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls417-il | 200,000 | 5 | 61.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls417-il | 500,000 | 9 | 92.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls417-il | 500,000 | 5 | 82.1 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls417-il | 1,000,000 | 9 | 112.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls417-il | 1,000,000 | 5 | 91.3 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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