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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(m2-il) NACA M2 AIRFOIL | NACA/Munk M-2 airfoil Max thickness 8% at 30% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
(hq3514-il) HQ 3.5/14 AIRFOIL | Quabeck HQ 3.5/14 R/C sailplane airfoil Max thickness 14% at 35% chord Max camber 3.5% at 50% chord | Remove Airfoil details Airfoil plotter |
(ls013-il) NASA/LANGLEY LS(1)-0013 AIRFOIL | NASA/Langley LS(1)-0013 general aviation airfoil Max thickness 12.9% at 40% chord Max camber 0% at 0% chord | Remove Airfoil details Airfoil plotter |
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Polars for (m2-il,hq3514-il,ls013-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m2-il | 50,000 | 9 | 21.8 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m2-il | 50,000 | 5 | 21.6 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m2-il | 100,000 | 9 | 29.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m2-il | 100,000 | 5 | 27.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m2-il | 200,000 | 9 | 32 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m2-il | 200,000 | 5 | 36.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m2-il | 500,000 | 9 | 45.9 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m2-il | 500,000 | 5 | 54.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m2-il | 1,000,000 | 9 | 60.6 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m2-il | 1,000,000 | 5 | 70.2 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3514-il | 50,000 | 9 | 29.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3514-il | 50,000 | 5 | 33.1 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3514-il | 100,000 | 9 | 55.8 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3514-il | 100,000 | 5 | 54.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3514-il | 200,000 | 9 | 80 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3514-il | 200,000 | 5 | 71.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3514-il | 500,000 | 9 | 100.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3514-il | 500,000 | 5 | 86.3 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| hq3514-il | 1,000,000 | 9 | 112.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| hq3514-il | 1,000,000 | 5 | 99.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls013-il | 50,000 | 9 | 26.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls013-il | 50,000 | 5 | 25.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls013-il | 100,000 | 9 | 36.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls013-il | 100,000 | 5 | 30.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls013-il | 200,000 | 9 | 39.8 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls013-il | 200,000 | 5 | 39.9 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls013-il | 500,000 | 9 | 52.7 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls013-il | 500,000 | 5 | 57.2 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ls013-il | 1,000,000 | 9 | 69.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ls013-il | 1,000,000 | 5 | 71.7 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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