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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(tempest1-il) HAWKER TEMPEST 37.5% SEMISPAN AIRFOIL | Hawker Tempest 37.5% semispan airfoil (NPL?) Max thickness 14.5% at 38.3% chord Max camber 1% at 40.4% chord | Remove Airfoil details Airfoil plotter |
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Polars for (tempest1-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| tempest1-il | 50,000 | 9 | 30.9 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tempest1-il | 50,000 | 5 | 30.2 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tempest1-il | 100,000 | 9 | 49.8 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tempest1-il | 100,000 | 5 | 47.7 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tempest1-il | 200,000 | 9 | 67 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tempest1-il | 200,000 | 5 | 53.7 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tempest1-il | 500,000 | 9 | 71.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tempest1-il | 500,000 | 5 | 62.2 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| tempest1-il | 1,000,000 | 9 | 81.5 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| tempest1-il | 1,000,000 | 5 | 68.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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