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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(usa46-il) USA 46 AIRFOIL | USA-46 airfoil Max thickness 6.5% at 20% chord Max camber 2.2% at 40% chord | Remove Airfoil details Airfoil plotter |
(v23010-il) BOEING-VERTOL V23010-1.58 AIRFOIL | Boeing-Vertol V23010-1.58 rotorcraft airfoil Max thickness 10.2% at 30% chord Max camber 1.8% at 15% chord | Remove Airfoil details Airfoil plotter |
(goe591-il) GOE 591 AIRFOIL | Gottingen 591 airfoil Max thickness 11.2% at 30% chord Max camber 5.1% at 40% chord | Remove Airfoil details Airfoil plotter |
(goe483-il) GOE 483 AIRFOIL | Gottingen 483 airfoil Max thickness 5.5% at 15% chord Max camber 5.8% at 40% chord | Remove Airfoil details Airfoil plotter |
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Polars for (usa46-il,v23010-il,goe591-il,goe483-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| usa46-il | 50,000 | 9 | 38.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa46-il | 50,000 | 5 | 38.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa46-il | 100,000 | 9 | 52.9 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa46-il | 100,000 | 5 | 51.8 at α=4° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa46-il | 200,000 | 9 | 69 at α=3.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa46-il | 200,000 | 5 | 63.6 at α=3.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa46-il | 500,000 | 9 | 86.4 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa46-il | 500,000 | 5 | 75.1 at α=2.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| usa46-il | 1,000,000 | 9 | 97.3 at α=2.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| usa46-il | 1,000,000 | 5 | 80.8 at α=3° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v23010-il | 50,000 | 9 | 23.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v23010-il | 50,000 | 5 | 27.9 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v23010-il | 100,000 | 9 | 35.1 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v23010-il | 100,000 | 5 | 41.2 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v23010-il | 200,000 | 9 | 54.2 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v23010-il | 200,000 | 5 | 57.7 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v23010-il | 500,000 | 9 | 79.9 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v23010-il | 500,000 | 5 | 78 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| v23010-il | 1,000,000 | 9 | 97.6 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| v23010-il | 1,000,000 | 5 | 94.1 at α=8.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe591-il | 50,000 | 9 | 16 at α=14.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe591-il | 50,000 | 5 | 34.4 at α=7.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe591-il | 100,000 | 9 | 52.7 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe591-il | 100,000 | 5 | 57.3 at α=6.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe591-il | 200,000 | 9 | 77.2 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe591-il | 200,000 | 5 | 76.9 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe591-il | 500,000 | 9 | 108 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe591-il | 500,000 | 5 | 103.1 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe591-il | 1,000,000 | 9 | 132.3 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe591-il | 1,000,000 | 5 | 122.7 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe483-il | 50,000 | 9 | 42.8 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe483-il | 50,000 | 5 | 44.6 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe483-il | 100,000 | 9 | 62.7 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe483-il | 100,000 | 5 | 65.1 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe483-il | 200,000 | 9 | 83.8 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe483-il | 200,000 | 5 | 85.6 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe483-il | 500,000 | 9 | 114.3 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe483-il | 500,000 | 5 | 112.3 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| goe483-il | 1,000,000 | 9 | 137.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| goe483-il | 1,000,000 | 5 | 121.9 at α=4.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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