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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(naca23024-il) NACA 23024 | NACA 23024 airfoil Max thickness 24% at 30.3% chord Max camber 2.9% at 1.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca23024-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca23024-il | 50,000 | 9 | 16.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23024-il | 50,000 | 5 | 19.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23024-il | 100,000 | 9 | 34.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23024-il | 100,000 | 5 | 28.5 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23024-il | 200,000 | 9 | 41.3 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23024-il | 200,000 | 5 | 33.2 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23024-il | 500,000 | 9 | 44.5 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23024-il | 500,000 | 5 | 43.4 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca23024-il | 1,000,000 | 9 | 56.9 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca23024-il | 1,000,000 | 5 | 54.4 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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