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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(vr8-il) BOEING-VERTOL VR-8 AIRFOIL | Boeing-Vertol VR-8 rotorcraft airfoil Max thickness 8.2% at 35% chord Max camber 1.3% at 35% chord | Remove Airfoil details Airfoil plotter |
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Polars for (vr8-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| vr8-il | 50,000 | 9 | 33.2 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr8-il | 50,000 | 5 | 31.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr8-il | 100,000 | 9 | 44.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr8-il | 100,000 | 5 | 38.7 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr8-il | 200,000 | 9 | 51.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr8-il | 200,000 | 5 | 44.3 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr8-il | 500,000 | 9 | 56.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr8-il | 500,000 | 5 | 53.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| vr8-il | 1,000,000 | 9 | 123.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| vr8-il | 1,000,000 | 5 | 60.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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