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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(ah93156-il) AH 93-156 | Althaus AH 93-156 airfoil Max thickness 15.7% at 39.5% chord Max camber 3.7% at 41.5% chord | Remove Airfoil details Airfoil plotter |
(naca747a315-il) NACA 747A315 | NACA 747A315 airfoil Max thickness 15% at 40.2% chord Max camber 2.5% at 35% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ah93156-il,naca747a315-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah93156-il | 50,000 | 9 | 4.8 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93156-il | 50,000 | 5 | 15.6 at α=12° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93156-il | 100,000 | 9 | 39 at α=11.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93156-il | 100,000 | 5 | 35.5 at α=10.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93156-il | 200,000 | 9 | 72.1 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93156-il | 200,000 | 5 | 64.7 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93156-il | 500,000 | 9 | 103.1 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93156-il | 500,000 | 5 | 94.1 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah93156-il | 1,000,000 | 9 | 125 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah93156-il | 1,000,000 | 5 | 114.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a315-il | 50,000 | 9 | 20.2 at α=10.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a315-il | 50,000 | 5 | 17.3 at α=2° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a315-il | 100,000 | 9 | 44.4 at α=8.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a315-il | 100,000 | 5 | 46.4 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a315-il | 200,000 | 9 | 72 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a315-il | 200,000 | 5 | 61.6 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a315-il | 500,000 | 9 | 89.8 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a315-il | 500,000 | 5 | 85.1 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| naca747a315-il | 1,000,000 | 9 | 111.5 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| naca747a315-il | 1,000,000 | 5 | 100.3 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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