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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(dae51-il) DAE-51 AIRFOIL | Drela DAE51 low Reynolds number airfoil Max thickness 9.4% at 30.7% chord Max camber 4% at 46.4% chord | Remove Airfoil details Airfoil plotter |
(b737b-il) BOEING 737 MIDSPAN AIRFOIL | Boeing Commercial Airplane Company model 737 airfoils Max thickness 12.5% at 29.7% chord Max camber 0.8% at 10% chord | Remove Airfoil details Airfoil plotter |
(cap21c-il) CAP 21 (TraCFoil) | CAP 21 (TraCFoil) airfoil Max thickness 15.6% at 15.7% chord Max camber 0.6% at 23.9% chord | Remove Airfoil details Airfoil plotter |
(c5a-il) LOCKHEED C-5A BL0 AIRFOIL | Lockheed-Georgia C-5A transonic wing airfoils Max thickness 13.1% at 40% chord Max camber 0.7% at 85% chord | Remove Airfoil details Airfoil plotter |
(e407-il) EPPLER 407 AIRFOIL | Eppler E407 sailplane airfoil Max thickness 14.4% at 36.6% chord Max camber 3.5% at 71.7% chord | Remove Airfoil details Airfoil plotter |
(fx3-il) WORTMANN FX 3 AIRFOIL | Wortmann FX 3 airfoil Max thickness 20% at 50% chord Max camber 4.2% at 75% chord | Remove Airfoil details Airfoil plotter |
(goe655-il) GOE 655 AIRFOIL | Gottingen 655 airfoil Max thickness 13.9% at 30% chord Max camber 4.4% at 40% chord | Remove Airfoil details Airfoil plotter |
(e862-il) EPPLER 862 STRUT AIRFOIL | Eppler E862 strut airfoil Max thickness 32.4% at 28.5% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (dae51-il,b737b-il,cap21c-il,c5a-il,e407-il,fx3-il,goe655-il,e862-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| dae51-il | 50,000 | 9 | 39.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae51-il | 50,000 | 5 | 41 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae51-il | 100,000 | 9 | 62.6 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae51-il | 100,000 | 5 | 63.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae51-il | 200,000 | 9 | 87.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae51-il | 200,000 | 5 | 84.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae51-il | 500,000 | 9 | 121.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae51-il | 500,000 | 5 | 110.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| dae51-il | 1,000,000 | 9 | 144.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| dae51-il | 1,000,000 | 5 | 127.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737b-il | 50,000 | 9 | 23.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737b-il | 50,000 | 5 | 26.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737b-il | 100,000 | 9 | 34.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737b-il | 100,000 | 5 | 37.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737b-il | 200,000 | 9 | 47.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737b-il | 200,000 | 5 | 51 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737b-il | 500,000 | 9 | 69.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737b-il | 500,000 | 5 | 71.2 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| b737b-il | 1,000,000 | 9 | 88.7 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| b737b-il | 1,000,000 | 5 | 87.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cap21c-il | 50,000 | 9 | 9.9 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cap21c-il | 50,000 | 5 | 14.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cap21c-il | 100,000 | 9 | 17.1 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cap21c-il | 100,000 | 5 | 26 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cap21c-il | 200,000 | 9 | 38.4 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cap21c-il | 200,000 | 5 | 48.1 at α=11.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cap21c-il | 500,000 | 9 | 74 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cap21c-il | 500,000 | 5 | 77.6 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cap21c-il | 1,000,000 | 9 | 97.4 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cap21c-il | 1,000,000 | 5 | 97.4 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5a-il | 50,000 | 9 | 27.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5a-il | 50,000 | 5 | 27.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5a-il | 100,000 | 9 | 41.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5a-il | 100,000 | 5 | 32.5 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5a-il | 200,000 | 9 | 44.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5a-il | 200,000 | 5 | 40.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5a-il | 500,000 | 9 | 56.8 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5a-il | 500,000 | 5 | 55.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| c5a-il | 1,000,000 | 9 | 68.9 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| c5a-il | 1,000,000 | 5 | 72.3 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e407-il | 50,000 | 9 | 34.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e407-il | 50,000 | 5 | 30.9 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e407-il | 100,000 | 9 | 50.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e407-il | 100,000 | 5 | 48.2 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e407-il | 200,000 | 9 | 72 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e407-il | 200,000 | 5 | 72 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e407-il | 500,000 | 9 | 113 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e407-il | 500,000 | 5 | 104.1 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e407-il | 1,000,000 | 9 | 144.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e407-il | 1,000,000 | 5 | 121.5 at α=1.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx3-il | 50,000 | 5 | 15.4 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx3-il | 50,000 | 0 | 18.5 at α=12.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx3-il | 100,000 | 5 | 23.4 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx3-il | 100,000 | 0 | 23.4 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx3-il | 200,000 | 5 | 32.9 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx3-il | 200,000 | 0 | 31.7 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx3-il | 500,000 | 5 | 44.6 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx3-il | 500,000 | 0 | 40.9 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx3-il | 1,000,000 | 5 | 58.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx3-il | 1,000,000 | 0 | 54.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe655-il | 50,000 | 9 | 16.1 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe655-il | 50,000 | 5 | 32.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe655-il | 100,000 | 9 | 45.6 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe655-il | 100,000 | 5 | 49 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe655-il | 200,000 | 9 | 64.5 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe655-il | 200,000 | 5 | 64.9 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe655-il | 500,000 | 9 | 91.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe655-il | 500,000 | 5 | 89.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe655-il | 1,000,000 | 9 | 115.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe655-il | 1,000,000 | 5 | 109 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e862-il | 50,000 | 9 | 2.8 at α=-4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e862-il | 50,000 | 5 | 2.6 at α=-2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e862-il | 100,000 | 9 | 5.1 at α=-0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e862-il | 100,000 | 5 | 10.5 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e862-il | 200,000 | 9 | 20.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e862-il | 200,000 | 5 | 32.7 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e862-il | 500,000 | 9 | 57.1 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e862-il | 500,000 | 5 | 54.9 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e862-il | 1,000,000 | 9 | 78.1 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e862-il | 1,000,000 | 5 | 74.9 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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