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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(v13006-il) BOEING VERTOL V13006-.7 AIRFOIL | Boeing-Vertol V13006-.7 rotorcraft airfoil Max thickness 6% at 30.2% chord Max camber 0.9% at 20.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (v13006-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| v13006-il | 50,000 | 9 | 27.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13006-il | 50,000 | 5 | 28.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v13006-il | 100,000 | 9 | 37.7 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13006-il | 100,000 | 5 | 35.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v13006-il | 200,000 | 9 | 46.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13006-il | 200,000 | 5 | 41.1 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v13006-il | 500,000 | 9 | 54.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13006-il | 500,000 | 5 | 53.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v13006-il | 1,000,000 | 9 | 62.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v13006-il | 1,000,000 | 5 | 64.2 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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