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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(rc0864c-il) NASA/LANGLEY RC08-64C AIRFOIL | NASA/Langley 08-64C rotorcraft airfoil Max thickness 8% at 40% chord Max camber 1% at 35% chord | Remove Airfoil details Airfoil plotter |
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Polars for (rc0864c-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| rc0864c-il | 50,000 | 9 | 23.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc0864c-il | 50,000 | 5 | 25.4 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc0864c-il | 100,000 | 9 | 37.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc0864c-il | 100,000 | 5 | 31.8 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc0864c-il | 200,000 | 9 | 44 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc0864c-il | 200,000 | 5 | 33.8 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc0864c-il | 500,000 | 9 | 42.7 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc0864c-il | 500,000 | 5 | 40.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| rc0864c-il | 1,000,000 | 9 | 45.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| rc0864c-il | 1,000,000 | 5 | 46.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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