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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(n6h20-il) NACA 6-H-20 AIRFOIL | NACA 6-H-20 rotorcraft airfoil Max thickness 20% at 40% chord Max camber 6.1% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (n6h20-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n6h20-il | 50,000 | 9 | 3.5 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6h20-il | 50,000 | 5 | 6.1 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6h20-il | 100,000 | 9 | 6 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6h20-il | 100,000 | 5 | 8.5 at α=15° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6h20-il | 200,000 | 9 | 16.8 at α=16.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6h20-il | 200,000 | 5 | 14.2 at α=15° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6h20-il | 500,000 | 9 | 67.6 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6h20-il | 500,000 | 5 | 50.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6h20-il | 1,000,000 | 9 | 83 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6h20-il | 1,000,000 | 5 | 81.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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