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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(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 |
(jn153-il) JN-153 AIRFOIL | Narramore JN153 airfoil Max thickness 17.6% at 28.2% chord Max camber 8.4% at 38.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (hobiesm-il,jn153-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| jn153-il | 50,000 | 9 | 4.6 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| jn153-il | 50,000 | 5 | 6.5 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| jn153-il | 100,000 | 9 | 5.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| jn153-il | 100,000 | 5 | 18.1 at α=1.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| jn153-il | 200,000 | 9 | 16.6 at α=1.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| jn153-il | 200,000 | 5 | 44.6 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| jn153-il | 500,000 | 9 | 98.8 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| jn153-il | 500,000 | 5 | 112.6 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| jn153-il | 1,000,000 | 9 | 163.3 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| jn153-il | 1,000,000 | 5 | 165.9 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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