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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(n1h15-il) NACA 1-H-15 AIRFOIL | NACA 1-H-15 rotorcraft airfoil Max thickness 14.7% at 40% chord Max camber 5.5% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (n1h15-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n1h15-il | 50,000 | 9 | 18.6 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n1h15-il | 50,000 | 5 | 12.6 at α=15.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n1h15-il | 100,000 | 9 | 20.3 at α=14° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n1h15-il | 100,000 | 5 | 19.2 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n1h15-il | 200,000 | 9 | 29 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n1h15-il | 200,000 | 5 | 31.1 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n1h15-il | 500,000 | 9 | 103.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n1h15-il | 500,000 | 5 | 102.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n1h15-il | 1,000,000 | 9 | 150.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n1h15-il | 1,000,000 | 5 | 133.2 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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