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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(n6h15-il) NACA 6-H-15 AIRFOIL | NACA 6-H-15 rotorcraft airfoil Max thickness 15.6% at 40% chord Max camber 4.5% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (n6h15-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n6h15-il | 50,000 | 9 | 15.5 at α=14.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6h15-il | 50,000 | 5 | 10.7 at α=13.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6h15-il | 100,000 | 9 | 17.3 at α=15° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6h15-il | 100,000 | 5 | 23.1 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6h15-il | 200,000 | 9 | 64.8 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6h15-il | 200,000 | 5 | 53.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6h15-il | 500,000 | 9 | 85.1 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6h15-il | 500,000 | 5 | 83 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n6h15-il | 1,000,000 | 9 | 109.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n6h15-il | 1,000,000 | 5 | 97.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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