Airfoil Comparison
Select airfoils from the airfoil database or add your own airfoils and compare the airfoil shape and lift/drag polars.
| Open full size plan in new window | Open paginated plan in new window | |
| Download PDF file | SVG image as text file | |
| Clear all | ||
(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 |
Drawing Options
Polars for (boe103-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 | |
| Reynolds number calculator | |||||||