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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(rc10n1-il) NASA/LANGLEY RC-10(N)1 AIRFOIL | NASA/Langley RC-10(N)1 rotorcraft airfoil Max thickness 10% at 37.6% chord Max camber 1.5% at 25% chord | Remove Airfoil details Airfoil plotter |
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Polars for (rc10n1-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rc10n1-il | 50,000 | 9 | 33.3 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc10n1-il | 50,000 | 5 | 33.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc10n1-il | 100,000 | 9 | 49 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc10n1-il | 100,000 | 5 | 46.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc10n1-il | 200,000 | 9 | 65.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc10n1-il | 200,000 | 5 | 59.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc10n1-il | 500,000 | 9 | 84.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc10n1-il | 500,000 | 5 | 70.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc10n1-il | 1,000,000 | 9 | 94.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc10n1-il | 1,000,000 | 5 | 78.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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