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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(boe106-il) BOEING 106 AIRFOIL | Boeing 106 airfoil Max thickness 13.1% at 30% chord Max camber 3.3% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (boe106-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| boe106-il | 50,000 | 9 | 29.7 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| boe106-il | 50,000 | 5 | 32.5 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| boe106-il | 100,000 | 9 | 51.6 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| boe106-il | 100,000 | 5 | 52.8 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| boe106-il | 200,000 | 9 | 72.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| boe106-il | 200,000 | 5 | 70.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| boe106-il | 500,000 | 9 | 98.8 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| boe106-il | 500,000 | 5 | 92 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| boe106-il | 1,000,000 | 9 | 118.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| boe106-il | 1,000,000 | 5 | 108.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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