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 |
(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 |
(marske1-il) MARSKE XM-1D AIRFOIL (F14-3.0) | Marske XM-1D airfoil (F14-3.0) Max thickness 14% at 25.1% chord Max camber 3% at 25.1% chord | Remove Airfoil details Airfoil plotter |
(marske3-il) MARSKE PIONEER IID ROOT AIRFOIL (NACA 431012A/24112 HYBRID) | Marske Pioneer IID root airfoil (NACA 43012A/24112 hybrid) Max thickness 12.1% at 30% chord Max camber 2.8% at 15% chord | Remove Airfoil details Airfoil plotter |
(marske5-il) MARSKE MONARCH AIRFOIL (NACA 43012A) | Marske Monarch airfoil (NACA 43012A) Max thickness 12.2% at 20% chord Max camber 3.4% at 15% chord | Remove Airfoil details Airfoil plotter |
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Polars for (m5-il,m4-il,marske1-il,marske3-il,marske5-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 | |
| 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 | |
| marske1-il | 50,000 | 9 | 9.4 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske1-il | 50,000 | 5 | 17.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marske1-il | 100,000 | 9 | 21.7 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske1-il | 100,000 | 5 | 38.4 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marske1-il | 200,000 | 9 | 55.7 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske1-il | 200,000 | 5 | 60.4 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marske1-il | 500,000 | 9 | 89.8 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske1-il | 500,000 | 5 | 88.8 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marske1-il | 1,000,000 | 9 | 115.3 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske1-il | 1,000,000 | 5 | 104.7 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marske3-il | 50,000 | 9 | 19 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske3-il | 50,000 | 5 | 25 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marske3-il | 100,000 | 9 | 30.4 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske3-il | 100,000 | 5 | 37.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marske3-il | 200,000 | 9 | 46.3 at α=7° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske3-il | 200,000 | 5 | 54 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marske3-il | 500,000 | 9 | 75.4 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske3-il | 500,000 | 5 | 79 at α=10° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marske3-il | 1,000,000 | 9 | 99.8 at α=11° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske3-il | 1,000,000 | 5 | 97.8 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marske5-il | 50,000 | 9 | 15.7 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske5-il | 50,000 | 5 | 20.8 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marske5-il | 100,000 | 9 | 23.3 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske5-il | 100,000 | 5 | 31.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marske5-il | 200,000 | 9 | 36.1 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske5-il | 200,000 | 5 | 47.7 at α=8° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marske5-il | 500,000 | 9 | 65.1 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske5-il | 500,000 | 5 | 73.6 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| marske5-il | 1,000,000 | 9 | 92.9 at α=12.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| marske5-il | 1,000,000 | 5 | 96.5 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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