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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(m4-il) NACA M4 AIRFOIL | NACA/Munk M-4 airfoil Max thickness 6.3% at 30% chord Max camber 2.2% at 30% chord | Remove Airfoil details Airfoil plotter |
(m8-il) NACA M8 AIRFOIL | NACA/Munk M-8 airfoil Max thickness 11.7% at 15% chord Max camber 8% at 30% chord | Remove Airfoil details Airfoil plotter |
(m685-il) M6 (85%) | NACA/Munk M6 (85%) Max thickness 10.2% at 30% chord Max camber 1.9% at 30% chord | Remove Airfoil details Airfoil plotter |
(marsden-il) Marsden | Marsden airfoil Max thickness 27.9% at 31.6% chord Max camber 7.7% at 37.6% chord | Remove Airfoil details Airfoil plotter |
(marske7-il) RONCZ LOW DRAG FLYING WING AIRFOIL | Roncz/Marske-7 low drag flying wing airfoil Max thickness 12.1% at 42.8% chord Max camber 2.8% at 39.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (m4-il,m8-il,m685-il,marsden-il,marske7-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| m4-il | 50,000 | 9 | 33.1 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m4-il | 50,000 | 5 | 34 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m4-il | 100,000 | 9 | 45.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m4-il | 100,000 | 5 | 44.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m4-il | 200,000 | 9 | 57.3 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m4-il | 200,000 | 5 | 55.4 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m4-il | 500,000 | 9 | 71.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m4-il | 500,000 | 5 | 66.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m4-il | 1,000,000 | 9 | 80.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m4-il | 1,000,000 | 5 | 73.3 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m8-il | 50,000 | 9 | 8.5 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m8-il | 50,000 | 5 | 26.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m8-il | 100,000 | 9 | 40.4 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m8-il | 100,000 | 5 | 46.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m8-il | 200,000 | 9 | 60.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m8-il | 200,000 | 5 | 62.1 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m8-il | 500,000 | 9 | 83 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m8-il | 500,000 | 5 | 79.6 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m8-il | 1,000,000 | 9 | 96.6 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m8-il | 1,000,000 | 5 | 99.1 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m685-il | 50,000 | 9 | 33.2 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m685-il | 50,000 | 5 | 34.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m685-il | 100,000 | 9 | 50.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m685-il | 100,000 | 5 | 49.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m685-il | 200,000 | 9 | 66.9 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m685-il | 200,000 | 5 | 62.9 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m685-il | 500,000 | 9 | 84.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m685-il | 500,000 | 5 | 70.7 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| m685-il | 1,000,000 | 9 | 85.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| m685-il | 1,000,000 | 5 | 75.1 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marsden-il | 50,000 | 9 | 3 at α=14.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marsden-il | 50,000 | 5 | 3.5 at α=13.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marsden-il | 100,000 | 9 | 3 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marsden-il | 100,000 | 5 | 4.7 at α=-10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marsden-il | 200,000 | 9 | 5.1 at α=-8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marsden-il | 200,000 | 5 | 17 at α=-2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marsden-il | 500,000 | 9 | 28.7 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marsden-il | 500,000 | 5 | 59.1 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marsden-il | 1,000,000 | 9 | 70.2 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marsden-il | 1,000,000 | 5 | 98 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marske7-il | 50,000 | 9 | 27.4 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske7-il | 50,000 | 5 | 24 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marske7-il | 100,000 | 9 | 43.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske7-il | 100,000 | 5 | 43.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marske7-il | 200,000 | 9 | 72 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske7-il | 200,000 | 5 | 67.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marske7-il | 500,000 | 9 | 103.7 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske7-il | 500,000 | 5 | 90.8 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marske7-il | 1,000,000 | 9 | 120.8 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske7-il | 1,000,000 | 5 | 96.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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