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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(rc1264c-il) NASA/LANGLEY RC12-64C AIRFOIL | NASA/Langley 12-64C rotorcraft airfoil Max thickness 12% at 40% chord Max camber 1% at 35% chord | Remove Airfoil details Airfoil plotter |
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Polars for (rc1264c-il)
Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
---|---|---|---|---|---|---|---|
rc1264c-il | 50,000 | 9 | 31.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
rc1264c-il | 50,000 | 5 | 30 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
rc1264c-il | 100,000 | 9 | 46.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
rc1264c-il | 100,000 | 5 | 41.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
rc1264c-il | 200,000 | 9 | 58.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
rc1264c-il | 200,000 | 5 | 46.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
rc1264c-il | 500,000 | 9 | 61.1 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
rc1264c-il | 500,000 | 5 | 62.4 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
rc1264c-il | 1,000,000 | 9 | 76.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
rc1264c-il | 1,000,000 | 5 | 74.8 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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