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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(naca16015-il) NACA 16-015 | NACA 16-015 airfoil Max thickness 15% at 50% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(hq2512-il) HQ 2.5/12 AIRFOIL | Quabeck HQ 2.5/12 R/C sailplane airfoil Max thickness 12% at 35% chord Max camber 2.5% at 50% chord | Remove Airfoil details Airfoil plotter |
(usa34-il) USA 34 AIRFOIL | USA-34 airfoil Max thickness 18% at 29.5% chord Max camber 7.7% at 39.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (naca16015-il,hq2512-il,usa34-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| naca16015-il | 50,000 | 9 | 22.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16015-il | 50,000 | 5 | 21.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16015-il | 100,000 | 9 | 29.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16015-il | 100,000 | 5 | 28.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16015-il | 200,000 | 9 | 40.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16015-il | 200,000 | 5 | 32 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16015-il | 500,000 | 9 | 44.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16015-il | 500,000 | 5 | 39.7 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16015-il | 1,000,000 | 9 | 50.5 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16015-il | 1,000,000 | 5 | 50.5 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2512-il | 50,000 | 9 | 33.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2512-il | 50,000 | 5 | 36.1 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2512-il | 100,000 | 9 | 55.2 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2512-il | 100,000 | 5 | 53.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2512-il | 200,000 | 9 | 76.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2512-il | 200,000 | 5 | 70.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2512-il | 500,000 | 9 | 100.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2512-il | 500,000 | 5 | 83.7 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq2512-il | 1,000,000 | 9 | 108.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq2512-il | 1,000,000 | 5 | 92.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa34-il | 50,000 | 9 | 4 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa34-il | 50,000 | 5 | 9.2 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa34-il | 100,000 | 9 | 9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa34-il | 100,000 | 5 | 40.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa34-il | 200,000 | 9 | 66.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa34-il | 200,000 | 5 | 60.6 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa34-il | 500,000 | 9 | 86.6 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa34-il | 500,000 | 5 | 75 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa34-il | 1,000,000 | 9 | 104.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa34-il | 1,000,000 | 5 | 87.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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