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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(usa35-il) USA 35 AIRFOIL | USA-35 airfoil Max thickness 18.2% at 29.4% chord Max camber 6.4% at 39.4% chord | Remove Airfoil details Airfoil plotter |
(nacacyh-il) NACA CYH | NACA CYH airfoil Max thickness 11.7% at 30% chord Max camber 2.8% at 40% chord | Remove Airfoil details Airfoil plotter |
(fx05h126-il) WORTMANN FX 05-H-126 AIRFOIL | Wortmann FX 05-H-126 rotorcraft airfoil Max thickness 12.6% at 37.1% chord Max camber 4.4% at 37.1% chord | Remove Airfoil details Airfoil plotter |
(usa50-il) USA 50 AIRFOIL | USA-50 airfoil Max thickness 7% at 30% chord Max camber 2% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (usa35-il,nacacyh-il,fx05h126-il,usa50-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usa35-il | 50,000 | 9 | 4.3 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa35-il | 50,000 | 5 | 20.6 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa35-il | 100,000 | 9 | 35.4 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa35-il | 100,000 | 5 | 46.4 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa35-il | 200,000 | 9 | 66.5 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa35-il | 200,000 | 5 | 67 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa35-il | 500,000 | 9 | 97.7 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa35-il | 500,000 | 5 | 92.2 at α=4.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa35-il | 1,000,000 | 9 | 122.3 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa35-il | 1,000,000 | 5 | 109.5 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacacyh-il | 50,000 | 9 | 25.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacacyh-il | 50,000 | 5 | 33.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacacyh-il | 100,000 | 9 | 47.8 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacacyh-il | 100,000 | 5 | 49.4 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacacyh-il | 200,000 | 9 | 65.4 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacacyh-il | 200,000 | 5 | 64.7 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacacyh-il | 500,000 | 9 | 90.5 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacacyh-il | 500,000 | 5 | 87 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| nacacyh-il | 1,000,000 | 9 | 110.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| nacacyh-il | 1,000,000 | 5 | 101 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05h126-il | 50,000 | 9 | 19.1 at α=13.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05h126-il | 50,000 | 5 | 14.5 at α=12.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05h126-il | 100,000 | 9 | 25.1 at α=11.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05h126-il | 100,000 | 5 | 24.3 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05h126-il | 200,000 | 9 | 66.3 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05h126-il | 200,000 | 5 | 70.8 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05h126-il | 500,000 | 9 | 121.3 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05h126-il | 500,000 | 5 | 116.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx05h126-il | 1,000,000 | 9 | 158.3 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx05h126-il | 1,000,000 | 5 | 145.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa50-il | 50,000 | 9 | 36.4 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa50-il | 50,000 | 5 | 36.1 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa50-il | 100,000 | 9 | 51.1 at α=4° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa50-il | 100,000 | 5 | 49.2 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa50-il | 200,000 | 9 | 65.1 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa50-il | 200,000 | 5 | 60.5 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa50-il | 500,000 | 9 | 80.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa50-il | 500,000 | 5 | 73.3 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa50-il | 1,000,000 | 9 | 92.3 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa50-il | 1,000,000 | 5 | 83.7 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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