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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(p51droot-il) P-51D ROOT (BL17.5) AIRFOIL | P-51D root (BL17.5) airfoil Max thickness 16.5% at 38.9% chord Max camber 1.3% at 68.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (p51droot-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| p51droot-il | 50,000 | 9 | 28 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51droot-il | 50,000 | 5 | 23.9 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51droot-il | 100,000 | 9 | 46.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51droot-il | 100,000 | 5 | 43.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51droot-il | 200,000 | 9 | 62.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51droot-il | 200,000 | 5 | 57.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51droot-il | 500,000 | 9 | 81.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51droot-il | 500,000 | 5 | 71.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51droot-il | 1,000,000 | 9 | 92.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51droot-il | 1,000,000 | 5 | 79.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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