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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(nl722362-il) NLR-7223-62 AIRFOIL | NLR NLR-7223-62 transonic rotorcraft airfoil Max thickness 8.6% at 38% chord Max camber 1.3% at 21.6% chord | Remove Airfoil details Airfoil plotter |
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Polars for (nl722362-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| nl722362-il | 50,000 | 9 | 30 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nl722362-il | 50,000 | 5 | 28.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nl722362-il | 100,000 | 9 | 42.2 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nl722362-il | 100,000 | 5 | 39.8 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nl722362-il | 200,000 | 9 | 57.1 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nl722362-il | 200,000 | 5 | 52.9 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nl722362-il | 500,000 | 9 | 72.8 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nl722362-il | 500,000 | 5 | 70.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nl722362-il | 1,000,000 | 9 | 87.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nl722362-il | 1,000,000 | 5 | 78.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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