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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(ah82150a-il) AH 82-150 A | Althaus AH 82-150 A airfoil Max thickness 15% at 40.2% chord Max camber 3.3% at 43.5% chord | Remove Airfoil details Airfoil plotter |
(fx74cl5140-il) FX74_CL5_140 | Wortmann FX 74-CL5-140 high lift airfoil Max thickness 14% at 30.9% chord Max camber 9.9% at 37.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (ah82150a-il,fx74cl5140-il)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| ah82150a-il | 50,000 | 9 | 17.8 at α=13° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah82150a-il | 50,000 | 5 | 20.2 at α=10.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah82150a-il | 100,000 | 9 | 42.5 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah82150a-il | 100,000 | 5 | 41.9 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah82150a-il | 200,000 | 9 | 72.8 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah82150a-il | 200,000 | 5 | 73.4 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah82150a-il | 500,000 | 9 | 108.7 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah82150a-il | 500,000 | 5 | 107.4 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| ah82150a-il | 1,000,000 | 9 | 137.6 at α=5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| ah82150a-il | 1,000,000 | 5 | 129.9 at α=4.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 50,000 | 9 | 6.4 at α=5.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 50,000 | 5 | 18.3 at α=1° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 100,000 | 9 | 33.1 at α=0.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 100,000 | 5 | 46.8 at α=2.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 200,000 | 9 | 72.7 at α=10° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 200,000 | 5 | 73.8 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 500,000 | 9 | 118.8 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 500,000 | 5 | 115.5 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx74cl5140-il | 1,000,000 | 9 | 156.9 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx74cl5140-il | 1,000,000 | 5 | 149.7 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
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