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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(naca001264a08cli02-il) NACA 0012-64 a=0.8 c(li)=0.2 | NACA 0012-64 a=0.8 c(li)=0.2 airfoil Max thickness 11% at 39.9% chord Max camber 1.8% at 29.9% chord | Remove Airfoil details Airfoil plotter |
(p51dtip-il) P-51D TIP (BL215) AIRFOIL | P-51D tip (BL215) airfoil Max thickness 11.4% at 46.3% chord Max camber 1.3% at 46.3% chord | Remove Airfoil details Airfoil plotter |
(pw1211-pw) PW1211 | Peter Wick. Airfoil for plank model gliders Max thickness 7% at 24% chord Max camber 1.7% at 28.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca001264a08cli02-il,p51dtip-il,pw1211-pw)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca001264a08cli02-il | 50,000 | 9 | 33 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001264a08cli02-il | 50,000 | 5 | 32.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001264a08cli02-il | 100,000 | 9 | 49.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001264a08cli02-il | 100,000 | 5 | 48.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001264a08cli02-il | 200,000 | 9 | 66.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001264a08cli02-il | 200,000 | 5 | 61.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001264a08cli02-il | 500,000 | 9 | 80.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001264a08cli02-il | 500,000 | 5 | 63.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001264a08cli02-il | 1,000,000 | 9 | 77 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001264a08cli02-il | 1,000,000 | 5 | 72.5 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51dtip-il | 50,000 | 9 | 22.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51dtip-il | 50,000 | 5 | 23.2 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51dtip-il | 100,000 | 9 | 40.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51dtip-il | 100,000 | 5 | 35.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51dtip-il | 200,000 | 9 | 54.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51dtip-il | 200,000 | 5 | 49.4 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51dtip-il | 500,000 | 9 | 74.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51dtip-il | 500,000 | 5 | 63.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| p51dtip-il | 1,000,000 | 9 | 89.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| p51dtip-il | 1,000,000 | 5 | 68.4 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pw1211-pw | 50,000 | 9 | 27.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw1211-pw | 100,000 | 9 | 41.1 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw1211-pw | 200,000 | 9 | 55.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw1211-pw | 500,000 | 9 | 74.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw1211-pw | 1,000,000 | 9 | 87.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw1211-pw | 2,000,000 | 9 | 99.5 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pw1211-pw | 5,000,000 | 9 | 114.2 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
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