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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(boe103-il) BOEING 103 AIRFOIL | Boeing 103 airfoil Max thickness 12.7% at 30% chord Max camber 3.6% at 40% chord | Remove Airfoil details Airfoil plotter |
(e1233-il) EPPLER 1233 AIRFOIL | Eppler E1233 general aviation airfoil Max thickness 18.9% at 29.8% chord Max camber 4.4% at 29.8% chord | Remove Airfoil details Airfoil plotter |
(n5h15-il) NACA 5-H-15 AIRFOIL | NACA 5-H-15 rotorcraft airfoil Max thickness 15.4% at 40% chord Max camber 2.9% at 30% chord | Remove Airfoil details Airfoil plotter |
(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 |
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Polars for (boe103-il,e1233-il,n5h15-il,b707a-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| boe103-il | 50,000 | 9 | 32.6 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| boe103-il | 50,000 | 5 | 35 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| boe103-il | 100,000 | 9 | 53.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| boe103-il | 100,000 | 5 | 52.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| boe103-il | 200,000 | 9 | 72 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| boe103-il | 200,000 | 5 | 66.6 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| boe103-il | 500,000 | 9 | 94.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| boe103-il | 500,000 | 5 | 81.1 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| boe103-il | 1,000,000 | 9 | 107.9 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| boe103-il | 1,000,000 | 5 | 89 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1233-il | 50,000 | 9 | 15.7 at α=-1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1233-il | 50,000 | 5 | 21.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1233-il | 100,000 | 9 | 34 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1233-il | 100,000 | 5 | 41.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1233-il | 200,000 | 9 | 56.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1233-il | 200,000 | 5 | 58.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1233-il | 500,000 | 9 | 81 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1233-il | 500,000 | 5 | 81.3 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| e1233-il | 1,000,000 | 9 | 104.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| e1233-il | 1,000,000 | 5 | 103.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n5h15-il | 50,000 | 9 | 14.2 at α=14.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n5h15-il | 50,000 | 5 | 14.8 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n5h15-il | 100,000 | 9 | 30 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n5h15-il | 100,000 | 5 | 43.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n5h15-il | 200,000 | 9 | 70 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n5h15-il | 200,000 | 5 | 58.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n5h15-il | 500,000 | 9 | 78.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n5h15-il | 500,000 | 5 | 71.4 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n5h15-il | 1,000,000 | 9 | 92.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n5h15-il | 1,000,000 | 5 | 85.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| 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 | |
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