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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(hobie-il) HOBIE | Hobie Hawk airfoil (Hobie Hawk R/C sailplane) Max thickness 8.5% at 25% chord Max camber 4% at 45% chord | Remove Airfoil details Airfoil plotter |
(naca16018-il) NACA 16-018 | NACA 16-018 airfoil Max thickness 18% at 50% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(naca64a010-il) NACA 64A-010 10.0% | NACA 64A010 airfoil Max thickness 10% at 40% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(naca001066-il) NACA 0010-66 | NACA 0010-66 airfoil Max thickness 10% at 60% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(naca001034-il) NACA 0010-34 | NACA 0010-34 airfoil Max thickness 10% at 40% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hobie-il,naca16018-il,naca64a010-il,naca001066-il,naca001034-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| hobie-il | 50,000 | 9 | 40.8 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hobie-il | 50,000 | 5 | 41.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hobie-il | 100,000 | 9 | 59.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hobie-il | 100,000 | 5 | 60.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hobie-il | 200,000 | 9 | 78.8 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hobie-il | 200,000 | 5 | 76.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hobie-il | 500,000 | 9 | 100.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hobie-il | 500,000 | 5 | 93 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hobie-il | 1,000,000 | 9 | 115.1 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hobie-il | 1,000,000 | 5 | 102.7 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16018-il | 50,000 | 9 | 22.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16018-il | 50,000 | 5 | 20.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16018-il | 100,000 | 9 | 28.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16018-il | 100,000 | 5 | 24.4 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16018-il | 200,000 | 9 | 37.9 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16018-il | 200,000 | 5 | 30 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16018-il | 500,000 | 9 | 44.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16018-il | 500,000 | 5 | 33.3 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca16018-il | 1,000,000 | 9 | 47.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca16018-il | 1,000,000 | 5 | 40.5 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64a010-il | 50,000 | 9 | 26.6 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64a010-il | 50,000 | 5 | 26.2 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64a010-il | 100,000 | 9 | 37.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64a010-il | 100,000 | 5 | 34.5 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64a010-il | 200,000 | 9 | 46.6 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64a010-il | 200,000 | 5 | 36.9 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64a010-il | 500,000 | 9 | 50.8 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64a010-il | 500,000 | 5 | 49.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca64a010-il | 1,000,000 | 9 | 58.1 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca64a010-il | 1,000,000 | 5 | 63.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001066-il | 50,000 | 9 | 20.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001066-il | 50,000 | 5 | 21.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001066-il | 100,000 | 9 | 26.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001066-il | 100,000 | 5 | 28.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001066-il | 200,000 | 9 | 33.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001066-il | 200,000 | 5 | 34.4 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001066-il | 500,000 | 9 | 42.9 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001066-il | 500,000 | 5 | 47.1 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001066-il | 1,000,000 | 9 | 53.6 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001066-il | 1,000,000 | 5 | 59.7 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001034-il | 50,000 | 9 | 20.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001034-il | 50,000 | 5 | 25.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001034-il | 100,000 | 9 | 35.7 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001034-il | 100,000 | 5 | 34.8 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001034-il | 200,000 | 9 | 45.2 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001034-il | 200,000 | 5 | 38.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001034-il | 500,000 | 9 | 46.5 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001034-il | 500,000 | 5 | 43.9 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca001034-il | 1,000,000 | 9 | 49.7 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca001034-il | 1,000,000 | 5 | 51.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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