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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(fx73cl2152-il) FX 73-CL2-152 | Wortmann FX 73-CL2-152 airfoil Max thickness 15.2% at 22.2% chord Max camber 6.6% at 43.5% chord | Remove Airfoil details Airfoil plotter |
(cp-100-050-gn) Cambered plate C=10% T=5% R=1.3 | HAWT pipe blade with coordinates based on top surface. Camber=10% Wall thickness=5% Radius=1.3 Max thickness 7% at 4.2% chord Max camber 7.9% at 46.5% chord | Remove Airfoil details Airfoil plotter |
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Polars for (fx73cl2152-il,cp-100-050-gn)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| fx73cl2152-il | 50,000 | 9 | 16.3 at α=0° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 50,000 | 5 | 32.6 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl2152-il | 100,000 | 9 | 41.3 at α=2.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 100,000 | 5 | 52.8 at α=5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl2152-il | 200,000 | 9 | 66.3 at α=5.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 200,000 | 5 | 74.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl2152-il | 500,000 | 9 | 104.2 at α=6.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 500,000 | 5 | 107.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| fx73cl2152-il | 1,000,000 | 9 | 136.2 at α=7.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| fx73cl2152-il | 1,000,000 | 5 | 135.3 at α=7.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-100-050-gn | 50,000 | 9 | 27.5 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-100-050-gn | 50,000 | 5 | 23.9 at α=11° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-100-050-gn | 50,000 | 1 | 20 at α=7.25° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-100-050-gn | 100,000 | 9 | 31.4 at α=9.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-100-050-gn | 100,000 | 5 | 29 at α=10.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-100-050-gn | 100,000 | 1 | 30.4 at α=7° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-100-050-gn | 200,000 | 9 | 34.9 at α=9.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-100-050-gn | 200,000 | 5 | 33.9 at α=6.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-100-050-gn | 200,000 | 1 | 38.3 at α=6.25° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-100-050-gn | 500,000 | 9 | 42.8 at α=10.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-100-050-gn | 500,000 | 5 | 46 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-100-050-gn | 500,000 | 1 | 50.8 at α=6.25° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-100-050-gn | 1,000,000 | 9 | 48.2 at α=6.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-100-050-gn | 1,000,000 | 5 | 58.3 at α=6° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-100-050-gn | 1,000,000 | 1 | 62.1 at α=6° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
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