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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(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 |
(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 (marske7-il,marske5-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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 | |
| 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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