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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(tempest2-il) HAWKER TEMPEST 61% SEMISPAN AIRFOIL | Hawker Tempest 61% semispan airfoil (NPL?) Max thickness 12% at 37.3% chord Max camber 0.9% at 39.3% chord | Remove Airfoil details Airfoil plotter |
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Polars for (tempest2-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| tempest2-il | 50,000 | 9 | 32.6 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tempest2-il | 50,000 | 5 | 32 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tempest2-il | 100,000 | 9 | 49.9 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tempest2-il | 100,000 | 5 | 47.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tempest2-il | 200,000 | 9 | 65.6 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tempest2-il | 200,000 | 5 | 55 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tempest2-il | 500,000 | 9 | 71.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tempest2-il | 500,000 | 5 | 61.5 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tempest2-il | 1,000,000 | 9 | 79.5 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tempest2-il | 1,000,000 | 5 | 69.3 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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