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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(pfcm-il) PROPFAN CRUISE MISSILE WING AIRFOIL | Propfan Cruise Missile wing airfoil Max thickness 8.2% at 40% chord Max camber 1.3% at 50% chord | Remove Airfoil details Airfoil plotter |
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Polars for (pfcm-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| pfcm-il | 50,000 | 9 | 30.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pfcm-il | 50,000 | 5 | 33 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pfcm-il | 100,000 | 9 | 47 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pfcm-il | 100,000 | 5 | 44.9 at α=3.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pfcm-il | 200,000 | 9 | 61.6 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pfcm-il | 200,000 | 5 | 56.3 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pfcm-il | 500,000 | 5 | 67.3 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| pfcm-il | 500,000 | 0 | 78.7 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pfcm-il | 1,000,000 | 9 | 88.4 at α=2.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| pfcm-il | 1,000,000 | 5 | 70.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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