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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(bacxxx-il) BOEING BACXXX AIRFOIL | Boeing Commercial Airplane Company BACXXX Energy Efficient Transport Program airfoil Max thickness 11.3% at 35% chord Max camber 1.4% at 15% chord | Remove Airfoil details Airfoil plotter |
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Polars for (bacxxx-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| bacxxx-il | 50,000 | 9 | 31.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacxxx-il | 50,000 | 5 | 30.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacxxx-il | 100,000 | 9 | 44 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacxxx-il | 100,000 | 5 | 42.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacxxx-il | 200,000 | 9 | 58.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacxxx-il | 200,000 | 5 | 55.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacxxx-il | 500,000 | 9 | 75.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacxxx-il | 500,000 | 5 | 72.8 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacxxx-il | 1,000,000 | 9 | 90.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacxxx-il | 1,000,000 | 5 | 86.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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