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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(bacj-il) BOEING AIRFOIL J (no closed TE) | Boeing Commercial Airplane Company airfoil J Max thickness 10.1% at 40% chord Max camber 1.7% at 78% chord | Remove Airfoil details Airfoil plotter |
(ag08-il) AG08 | Drela AG08 airfoil Max thickness 5.8% at 21% chord Max camber 1.7% at 40.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (bacj-il,ag08-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| bacj-il | 50,000 | 9 | 20.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacj-il | 50,000 | 5 | 20.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacj-il | 100,000 | 9 | 27 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacj-il | 100,000 | 5 | 25 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacj-il | 200,000 | 9 | 31.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacj-il | 200,000 | 5 | -1 at α=-100° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| bacj-il | 500,000 | 9 | 51.8 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| bacj-il | 1,000,000 | 9 | 61.3 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag08-il | 50,000 | 9 | 32.8 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag08-il | 50,000 | 5 | 33.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag08-il | 100,000 | 9 | 45.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag08-il | 100,000 | 5 | 45.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag08-il | 200,000 | 9 | 58.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag08-il | 200,000 | 5 | 56.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag08-il | 500,000 | 9 | 76.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag08-il | 500,000 | 5 | 72 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag08-il | 1,000,000 | 9 | 89 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag08-il | 1,000,000 | 5 | 83.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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