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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(psu94097-il) PSU 94-097 (AIAA 2001-2478) | Maughmer PSU 94-097 winglet airfoil Max thickness 9.7% at 32.3% chord Max camber 4% at 46.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (psu94097-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| psu94097-il | 50,000 | 9 | 39.2 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| psu94097-il | 50,000 | 5 | 41.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| psu94097-il | 100,000 | 9 | 64 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| psu94097-il | 100,000 | 5 | 64.1 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| psu94097-il | 200,000 | 9 | 90.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| psu94097-il | 200,000 | 5 | 86.8 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| psu94097-il | 500,000 | 9 | 126.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| psu94097-il | 500,000 | 5 | 112.9 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| psu94097-il | 1,000,000 | 9 | 150.7 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| psu94097-il | 1,000,000 | 5 | 127.5 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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