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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(vr15-il) BOEING-VERTOL VR-15 AIRFOIL | Boeing-Vertol/Dadone VR-15 transonic rotorcraft airfoil Max thickness 8% at 35% chord Max camber 1.3% at 20% chord | Remove Airfoil details Airfoil plotter |
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Polars for (vr15-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| vr15-il | 50,000 | 9 | 28.1 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr15-il | 50,000 | 5 | 27.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr15-il | 100,000 | 9 | 38.2 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr15-il | 100,000 | 5 | 39 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr15-il | 200,000 | 9 | 49.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr15-il | 200,000 | 5 | 52 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr15-il | 500,000 | 9 | 70.9 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr15-il | 500,000 | 5 | 69.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr15-il | 1,000,000 | 9 | 85.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr15-il | 1,000,000 | 5 | 81.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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