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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(naca747a415-il) NACA 747A415 | NACA 747A415 airfoil Max thickness 15% at 40.2% chord Max camber 3% at 35% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca747a415-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca747a415-il | 50,000 | 9 | 19 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a415-il | 50,000 | 5 | 17 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a415-il | 100,000 | 9 | 37.4 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a415-il | 100,000 | 5 | 44.5 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a415-il | 200,000 | 9 | 73.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a415-il | 200,000 | 5 | 66.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a415-il | 500,000 | 9 | 97.5 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a415-il | 500,000 | 5 | 92.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a415-il | 1,000,000 | 9 | 120.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a415-il | 1,000,000 | 5 | 110.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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