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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(usa27m2-il) USA 27 mod. AIRFOIL | USA-27MOD airfoil Max thickness 13.3% at 30% chord Max camber 5% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (usa27m2-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usa27m2-il | 50,000 | 9 | 17.6 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27m2-il | 50,000 | 5 | 32.3 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa27m2-il | 100,000 | 9 | 47.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27m2-il | 100,000 | 5 | 48.6 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa27m2-il | 200,000 | 9 | 64.4 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27m2-il | 200,000 | 5 | 62.9 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa27m2-il | 500,000 | 9 | 86.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27m2-il | 500,000 | 5 | 85 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa27m2-il | 1,000,000 | 9 | 110 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27m2-il | 1,000,000 | 5 | 102.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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