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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(usa33-il) USA 33 AIRFOIL | USA-33 airfoil Max thickness 14.2% at 29.9% chord Max camber 4.9% at 29.9% chord | Remove Airfoil details Airfoil plotter |
(usa29-il) USA 29 AIRFOIL | USA-29 airfoil Max thickness 13.2% at 29.7% chord Max camber 5.5% at 39.7% chord | Remove Airfoil details Airfoil plotter |
(usa27-il) USA 27 AIRFOIL | USA-27 airfoil Max thickness 11.1% at 30% chord Max camber 5.1% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (usa33-il,usa29-il,usa27-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usa33-il | 50,000 | 9 | 7.2 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa33-il | 50,000 | 5 | 27.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa33-il | 100,000 | 9 | 45.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa33-il | 100,000 | 5 | 47.6 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa33-il | 200,000 | 9 | 66.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa33-il | 200,000 | 5 | 60.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa33-il | 500,000 | 9 | 85.3 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa33-il | 500,000 | 5 | 67.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa33-il | 1,000,000 | 9 | 93.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa33-il | 1,000,000 | 5 | 67.8 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa29-il | 50,000 | 9 | 6.6 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa29-il | 50,000 | 5 | 27.1 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa29-il | 100,000 | 9 | 50.4 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa29-il | 100,000 | 5 | 52.4 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa29-il | 200,000 | 9 | 74.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa29-il | 200,000 | 5 | 72.6 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa29-il | 500,000 | 9 | 90 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa29-il | 500,000 | 5 | 80.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa29-il | 1,000,000 | 9 | 101.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa29-il | 1,000,000 | 5 | 95.5 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa27-il | 50,000 | 9 | 20.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27-il | 50,000 | 5 | 35.5 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa27-il | 100,000 | 9 | 50.5 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27-il | 100,000 | 5 | 52.8 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa27-il | 200,000 | 9 | 69.4 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27-il | 200,000 | 5 | 69 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa27-il | 500,000 | 9 | 95.4 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27-il | 500,000 | 5 | 92 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa27-il | 1,000,000 | 9 | 117.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa27-il | 1,000,000 | 5 | 110.1 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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