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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(ms317-il) NASA/LANGLEY MS(1)-0317 AIRFOIL | NASA/Langley MS(1)-0317 general aviation airfoil Max thickness 17% at 37.5% chord Max camber 1.7% at 72.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ms317-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ms317-il | 50,000 | 9 | 28.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ms317-il | 50,000 | 5 | 24.2 at α=9.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ms317-il | 100,000 | 9 | 36.2 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ms317-il | 100,000 | 5 | 35.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ms317-il | 200,000 | 9 | 48.5 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ms317-il | 200,000 | 5 | 47.7 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ms317-il | 500,000 | 9 | 69.9 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ms317-il | 500,000 | 5 | 64.6 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ms317-il | 1,000,000 | 9 | 80.4 at α=1.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ms317-il | 1,000,000 | 5 | 80.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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