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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(m5-il) NACA M5 AIRFOIL | NACA/Munk M-5 airfoil Max thickness 8.2% at 30.1% chord Max camber 2.1% at 30.1% chord | Remove Airfoil details Airfoil plotter |
(ht12-il) HT12 | Drela HT12 airfoil Max thickness 5% at 18.6% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(ls417-il) NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL | NASA/Langley/Whitcomb LS(1)-0417 (GA(W)-1) general aviation airfoil Max thickness 17% at 40% chord Max camber 2.4% at 65% chord | Remove Airfoil details Airfoil plotter |
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Polars for (m5-il,ht12-il,ls417-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m5-il | 50,000 | 9 | 32.7 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m5-il | 50,000 | 5 | 34 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m5-il | 100,000 | 9 | 47.3 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m5-il | 100,000 | 5 | 46 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m5-il | 200,000 | 9 | 60.6 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m5-il | 200,000 | 5 | 57.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m5-il | 500,000 | 9 | 76.5 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m5-il | 500,000 | 5 | 70.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m5-il | 1,000,000 | 9 | 86.2 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m5-il | 1,000,000 | 5 | 76.7 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht12-il | 50,000 | 9 | 21.2 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht12-il | 50,000 | 5 | 20.3 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht12-il | 100,000 | 9 | 26.8 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht12-il | 100,000 | 5 | 26.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht12-il | 200,000 | 9 | 32.3 at α=3.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht12-il | 200,000 | 5 | 35.1 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht12-il | 500,000 | 9 | 45.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht12-il | 500,000 | 5 | 50.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ht12-il | 1,000,000 | 9 | 58.3 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ht12-il | 1,000,000 | 5 | 64.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls417-il | 50,000 | 9 | 29.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls417-il | 50,000 | 5 | 25 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls417-il | 100,000 | 9 | 42.9 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls417-il | 100,000 | 5 | 41 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls417-il | 200,000 | 9 | 61 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls417-il | 200,000 | 5 | 61.7 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls417-il | 500,000 | 9 | 92.9 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls417-il | 500,000 | 5 | 82.1 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls417-il | 1,000,000 | 9 | 112.6 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls417-il | 1,000,000 | 5 | 91.3 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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