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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(m15-il) NACA M15 AIRFOIL | NACA/Munk M-15 airfoil Max thickness 12% at 30% chord Max camber 3.8% at 30% chord | Remove Airfoil details Airfoil plotter |
(k2-il) GRUMMAN K-2 AIRFOIL | Grumman K-2 transonic airfoil (GAC .80-.53-10.3) Max thickness 10.3% at 38.9% chord Max camber 1.3% at 88.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (m15-il,k2-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m15-il | 50,000 | 9 | 23.8 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m15-il | 50,000 | 5 | 30 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m15-il | 100,000 | 9 | 50.3 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m15-il | 100,000 | 5 | 53.1 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m15-il | 200,000 | 9 | 72.2 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m15-il | 200,000 | 5 | 72.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m15-il | 500,000 | 9 | 101.6 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m15-il | 500,000 | 5 | 98.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m15-il | 1,000,000 | 9 | 124.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m15-il | 1,000,000 | 5 | 118.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k2-il | 50,000 | 9 | 21.7 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k2-il | 50,000 | 5 | 21.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k2-il | 100,000 | 9 | 28.9 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k2-il | 100,000 | 5 | 25.8 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k2-il | 200,000 | 9 | 29 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k2-il | 200,000 | 5 | 35.1 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k2-il | 500,000 | 9 | 44 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k2-il | 500,000 | 5 | 52.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| k2-il | 1,000,000 | 9 | 60.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| k2-il | 1,000,000 | 5 | 66.7 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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