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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(b707a-il) BOEING 707 .08 SPAN AIRFOIL | Boeing Commercial Airplane Company model 707 airfoils Max thickness 11.4% at 24% chord Max camber 0.2% at 6% chord | Remove Airfoil details Airfoil plotter |
(goe342-il) GOE 342 AIRFOIL | Gottingen 342 airfoil Max thickness 5.4% at 20% chord Max camber 6.2% at 40% chord | Remove Airfoil details Airfoil plotter |
(e168-il) E168 (12.45%) | Eppler E168 low Reynolds number airfoil Max thickness 12.4% at 26.7% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(e226-il) E226 (10.19%) | Eppler E226 low Reynolds number airfoil Max thickness 10.2% at 31.3% chord Max camber 0.5% at 56.9% 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 (b707a-il,goe342-il,e168-il,e226-il,ls417-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| b707a-il | 50,000 | 9 | 16.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707a-il | 50,000 | 5 | 20.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707a-il | 100,000 | 9 | 26.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707a-il | 100,000 | 5 | 32.2 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707a-il | 200,000 | 9 | 43.1 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707a-il | 200,000 | 5 | 43.6 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707a-il | 500,000 | 9 | 59.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707a-il | 500,000 | 5 | 52.4 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707a-il | 1,000,000 | 9 | 64.4 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707a-il | 1,000,000 | 5 | 59.4 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe342-il | 50,000 | 9 | 44.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe342-il | 50,000 | 5 | 47.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe342-il | 100,000 | 9 | 71.3 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe342-il | 100,000 | 5 | 71.4 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe342-il | 200,000 | 9 | 99.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe342-il | 200,000 | 5 | 85.9 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe342-il | 500,000 | 9 | 109.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe342-il | 500,000 | 5 | 105.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe342-il | 1,000,000 | 9 | 130.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe342-il | 1,000,000 | 5 | 111.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e168-il | 50,000 | 9 | 22.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e168-il | 50,000 | 5 | 28 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e168-il | 100,000 | 9 | 38.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e168-il | 100,000 | 5 | 40.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e168-il | 200,000 | 9 | 53.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e168-il | 200,000 | 5 | 52.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e168-il | 500,000 | 9 | 73 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e168-il | 500,000 | 5 | 67.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e168-il | 1,000,000 | 9 | 87 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e168-il | 1,000,000 | 5 | 77.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e226-il | 50,000 | 9 | 30.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e226-il | 50,000 | 5 | 32.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e226-il | 100,000 | 9 | 45.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e226-il | 100,000 | 5 | 44.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e226-il | 200,000 | 9 | 59.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e226-il | 200,000 | 5 | 55.3 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e226-il | 500,000 | 9 | 77.1 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e226-il | 500,000 | 5 | 67.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e226-il | 1,000,000 | 9 | 86.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e226-il | 1,000,000 | 5 | 73.4 at α=5° | 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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