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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(nlr7301-il) NLR-7301 AIRFOIL | NLR NLR-7301 transonic airfoil Max thickness 16.5% at 35% chord Max camber 1.7% at 75% chord | Remove Airfoil details Airfoil plotter |
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Polars for (nlr7301-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| nlr7301-il | 50,000 | 9 | 21 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr7301-il | 50,000 | 5 | 18.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlr7301-il | 100,000 | 9 | 21.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr7301-il | 100,000 | 5 | 26.7 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlr7301-il | 200,000 | 9 | 31 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr7301-il | 200,000 | 5 | 37.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlr7301-il | 500,000 | 9 | 49.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr7301-il | 500,000 | 5 | 55.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nlr7301-il | 1,000,000 | 9 | 67.1 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nlr7301-il | 1,000,000 | 5 | 70.2 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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