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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(e1214-il) EPPLER 1214 AIRFOIL | Eppler E1214 general aviation airfoil Max thickness 19.8% at 26.2% chord Max camber 2.1% at 30.4% chord | Remove Airfoil details Airfoil plotter |
(e1210-il) EPPLER 1210 AIRFOIL | Eppler E1210 general aviation airfoil Max thickness 15.9% at 21.1% chord Max camber 5.2% at 33.3% chord | Remove Airfoil details Airfoil plotter |
(kc135winglet-il) KC-135 Winglet (supercritical Whitcomb) | Boeing KC-135 winglet airfoil designed by Richard T. Whitcomb Max thickness 8% at 40% chord Max camber 2.7% at 65% chord | Remove Airfoil details Airfoil plotter |
(j5012-il) J5012 12% | Jef Raskin (originator of the Apple Macintosh Project) J5012 airfoil Max thickness 12% at 34.5% chord Max camber 0% at 83.5% chord | Remove Airfoil details Airfoil plotter |
(b707e-il) BOEING 707 .99 SPAN AIRFOIL | Boeing Commercial Airplane Company model 707 airfoils Max thickness 9% at 42% chord Max camber 1.8% at 34% chord | Remove Airfoil details Airfoil plotter |
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Polars for (e1214-il,e1210-il,kc135winglet-il,j5012-il,b707e-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| e1214-il | 50,000 | 9 | 3.1 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1214-il | 50,000 | 5 | 18.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1214-il | 100,000 | 9 | 25.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1214-il | 100,000 | 5 | 36.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1214-il | 200,000 | 9 | 48.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1214-il | 200,000 | 5 | 54 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1214-il | 500,000 | 9 | 78.3 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1214-il | 500,000 | 5 | 80.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1214-il | 1,000,000 | 9 | 105.1 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1214-il | 1,000,000 | 5 | 103.9 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1210-il | 50,000 | 9 | 8.9 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1210-il | 50,000 | 5 | 25.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1210-il | 100,000 | 9 | 35.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1210-il | 100,000 | 5 | 45.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1210-il | 200,000 | 9 | 60.3 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1210-il | 200,000 | 5 | 65.1 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1210-il | 500,000 | 9 | 92.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1210-il | 500,000 | 5 | 93.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1210-il | 1,000,000 | 9 | 119.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1210-il | 1,000,000 | 5 | 117.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135winglet-il | 50,000 | 9 | 40.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135winglet-il | 50,000 | 5 | 40.9 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135winglet-il | 100,000 | 9 | 62.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135winglet-il | 100,000 | 5 | 59.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135winglet-il | 200,000 | 9 | 85.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135winglet-il | 200,000 | 5 | 73.2 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135winglet-il | 500,000 | 9 | 103.4 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135winglet-il | 500,000 | 5 | 88.7 at α=0.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| kc135winglet-il | 1,000,000 | 9 | 116.5 at α=1° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| kc135winglet-il | 1,000,000 | 5 | 89.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| j5012-il | 50,000 | 9 | 29 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| j5012-il | 50,000 | 5 | 28.2 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| j5012-il | 100,000 | 9 | 41.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| j5012-il | 100,000 | 5 | 38.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| j5012-il | 200,000 | 9 | 51.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| j5012-il | 200,000 | 5 | 45.7 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| j5012-il | 500,000 | 9 | 59.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| j5012-il | 500,000 | 5 | 58.9 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| j5012-il | 1,000,000 | 9 | 70.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| j5012-il | 1,000,000 | 5 | 70.4 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707e-il | 50,000 | 9 | 37 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707e-il | 50,000 | 5 | 35.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707e-il | 100,000 | 9 | 53.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707e-il | 100,000 | 5 | 48.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707e-il | 200,000 | 9 | 67.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707e-il | 200,000 | 5 | 53.6 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707e-il | 500,000 | 9 | 65.5 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707e-il | 500,000 | 5 | 64.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b707e-il | 1,000,000 | 9 | 77.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b707e-il | 1,000,000 | 5 | 75.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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