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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(n63215b-il) NACA 63(2)-215 MOD B | NACA-NASA/AMES/Hicks 63(2)-215 MOD B airfoil Max thickness 15% at 30% chord Max camber 1.5% at 10% chord | Remove Airfoil details Airfoil plotter |
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Polars for (n63215b-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n63215b-il | 50,000 | 9 | 25.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63215b-il | 50,000 | 5 | 24.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63215b-il | 100,000 | 9 | 32.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63215b-il | 100,000 | 5 | 35.3 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63215b-il | 200,000 | 9 | 44.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63215b-il | 200,000 | 5 | 47.9 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63215b-il | 500,000 | 9 | 66.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63215b-il | 500,000 | 5 | 68.3 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63215b-il | 1,000,000 | 9 | 86.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63215b-il | 1,000,000 | 5 | 83.9 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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