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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(ms313-il) NASA/LANGLEY MS(1)-0313 AIRFOIL | NASA/Langley MS(1)-0313 general aviation airfoil (buggy Max thickness 13.1% at 37.5% chord Max camber 1.8% at 67.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ms313-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ms313-il | 50,000 | 9 | 31.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ms313-il | 50,000 | 5 | 29.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ms313-il | 100,000 | 9 | 46.4 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ms313-il | 100,000 | 5 | 39.5 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ms313-il | 200,000 | 9 | 55.5 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ms313-il | 200,000 | 5 | 50.5 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ms313-il | 500,000 | 9 | 74.4 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ms313-il | 500,000 | 5 | 69.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ms313-il | 1,000,000 | 9 | 85.3 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ms313-il | 1,000,000 | 5 | 87.1 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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