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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(npl9660-il) NPL 9660 AIRFOIL | NPL 9660 rotorcraft airfoil Max thickness 11.3% at 34.2% chord Max camber 1% at 19.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (npl9660-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| npl9660-il | 50,000 | 9 | 28 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9660-il | 50,000 | 5 | 30.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9660-il | 100,000 | 9 | 41.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9660-il | 100,000 | 5 | 41.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9660-il | 200,000 | 9 | 54.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9660-il | 200,000 | 5 | 51.5 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9660-il | 500,000 | 9 | 69.7 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9660-il | 500,000 | 5 | 66.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| npl9660-il | 1,000,000 | 9 | 81.5 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| npl9660-il | 1,000,000 | 5 | 75.2 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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