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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(ag46ct02r-il) AG46ct -02f rot. | Drela AG46ct -02f airfoil Max thickness 6.1% at 23.3% chord Max camber 1.6% at 33% chord | Remove Airfoil details Airfoil plotter |
(ah93w215-il) AH 93-W-215 | Althaus AH 93-W-215 airfoil for use on wind turbines (W) Max thickness 21.2% at 33.9% chord Max camber 3.1% at 40.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ag46ct02r-il,ah93w215-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ag46ct02r-il | 50,000 | 9 | 30.8 at α=4.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag46ct02r-il | 50,000 | 5 | 33.3 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag46ct02r-il | 100,000 | 9 | 44.5 at α=4.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag46ct02r-il | 100,000 | 5 | 44.4 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag46ct02r-il | 200,000 | 9 | 58.2 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag46ct02r-il | 200,000 | 5 | 55.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag46ct02r-il | 500,000 | 9 | 74.9 at α=4.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag46ct02r-il | 500,000 | 5 | 72.5 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ag46ct02r-il | 1,000,000 | 9 | 88.6 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ag46ct02r-il | 1,000,000 | 5 | 86.2 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93w215-il | 50,000 | 9 | 2.7 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93w215-il | 50,000 | 5 | 6.4 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93w215-il | 100,000 | 9 | 6.2 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93w215-il | 100,000 | 5 | 27.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93w215-il | 200,000 | 9 | 57.6 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93w215-il | 200,000 | 5 | 58.8 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93w215-il | 500,000 | 9 | 93.8 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93w215-il | 500,000 | 5 | 79.2 at α=7.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93w215-il | 1,000,000 | 9 | 111.4 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93w215-il | 1,000,000 | 5 | 97.3 at α=7° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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