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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(n63210-il) NACA 63-210 AIRFOIL | NACA 63-210 airfoil Max thickness 10% at 35% chord Max camber 1.1% at 60% chord | Remove Airfoil details Airfoil plotter |
(trainer60-il) TRAINER60 | Great Planes R/C Trainer 60 airfoil Max thickness 18.3% at 27.1% chord Max camber 0.1% at 1.3% chord | Remove Airfoil details Airfoil plotter |
(hobiesm-il) HOBIESMO1.DAT | Hobie Hawk airfoil (Hobie Hawk R/C sailplane) Max thickness 8.6% at 25% chord Max camber 3.8% at 45% chord | Remove Airfoil details Airfoil plotter |
(n0009sm-il) NACA-0009 9.0% smoothed | NACA 0009 airfoil (smoothed) Max thickness 9% at 30.9% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (n63210-il,trainer60-il,hobiesm-il,n0009sm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| n63210-il | 50,000 | 9 | 33.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63210-il | 50,000 | 5 | 32 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63210-il | 100,000 | 9 | 46.7 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63210-il | 100,000 | 5 | 42.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63210-il | 200,000 | 9 | 59.4 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63210-il | 200,000 | 5 | 48.7 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63210-il | 500,000 | 9 | 67.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63210-il | 500,000 | 5 | 55.8 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n63210-il | 1,000,000 | 9 | 69 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n63210-il | 1,000,000 | 5 | 66.3 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| trainer60-il | 50,000 | 9 | 15.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| trainer60-il | 50,000 | 5 | 24.5 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| trainer60-il | 100,000 | 9 | 36.7 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| trainer60-il | 100,000 | 5 | 38.8 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| trainer60-il | 200,000 | 9 | 51.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| trainer60-il | 200,000 | 5 | 50.9 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| trainer60-il | 500,000 | 9 | 73.1 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| trainer60-il | 500,000 | 5 | 65.8 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| trainer60-il | 1,000,000 | 9 | 85.4 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| trainer60-il | 1,000,000 | 5 | 79.3 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hobiesm-il | 50,000 | 9 | 41.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hobiesm-il | 50,000 | 5 | 41.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hobiesm-il | 100,000 | 9 | 60.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hobiesm-il | 100,000 | 5 | 60.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hobiesm-il | 200,000 | 9 | 81.5 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hobiesm-il | 200,000 | 5 | 79 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hobiesm-il | 500,000 | 9 | 110 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hobiesm-il | 500,000 | 5 | 101.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hobiesm-il | 1,000,000 | 9 | 130.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hobiesm-il | 1,000,000 | 5 | 118.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n0009sm-il | 50,000 | 9 | 27 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n0009sm-il | 50,000 | 5 | 25.6 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n0009sm-il | 100,000 | 9 | 37.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n0009sm-il | 100,000 | 5 | 33.4 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n0009sm-il | 200,000 | 9 | 45.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n0009sm-il | 200,000 | 5 | 42.2 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n0009sm-il | 500,000 | 9 | 55.9 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n0009sm-il | 500,000 | 5 | 60.2 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| n0009sm-il | 1,000,000 | 9 | 74.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| n0009sm-il | 1,000,000 | 5 | 75.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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