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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(nn7mk20-il) NN7 MK20 | NN7 MK20 airfoil Max thickness 16.9% at 37.1% chord Max camber 3% at 59.8% chord | Remove Airfoil details Airfoil plotter |
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Polars for (nn7mk20-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| nn7mk20-il | 50,000 | 9 | 21 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nn7mk20-il | 50,000 | 5 | 17.2 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nn7mk20-il | 100,000 | 9 | 44.2 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nn7mk20-il | 100,000 | 5 | 43.8 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nn7mk20-il | 200,000 | 9 | 70.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nn7mk20-il | 200,000 | 5 | 69.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nn7mk20-il | 500,000 | 9 | 101.8 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nn7mk20-il | 500,000 | 5 | 99 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nn7mk20-il | 1,000,000 | 9 | 127.2 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nn7mk20-il | 1,000,000 | 5 | 118.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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