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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(cp-120-050-gn) Cambered plate C=12% T=5% R=1.1 | HAWT pipe blade with coordinates based on top surface. Camber=12% Wall thickness=5% Radius=1.102 Max thickness 6.1% at 4% chord Max camber 9.9% at 47.9% chord | Remove Airfoil details Airfoil plotter |
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Polars for (cp-120-050-gn)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| cp-120-050-gn | 50,000 | 9 | 25.2 at α=11.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-120-050-gn | 50,000 | 5 | 20.4 at α=12.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-120-050-gn | 50,000 | 1 | 19.1 at α=6° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-120-050-gn | 100,000 | 9 | 32.4 at α=6° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-120-050-gn | 100,000 | 5 | 29.5 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-120-050-gn | 100,000 | 1 | 27 at α=3.75° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-120-050-gn | 200,000 | 9 | 42.4 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-120-050-gn | 200,000 | 5 | 39.1 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-120-050-gn | 200,000 | 1 | 34.6 at α=6.5° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-120-050-gn | 500,000 | 9 | 42.8 at α=2° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-120-050-gn | 500,000 | 5 | 42.6 at α=5.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-120-050-gn | 500,000 | 1 | 46 at α=5.75° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-120-050-gn | 1,000,000 | 9 | 43.8 at α=5.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-120-050-gn | 1,000,000 | 5 | 53.7 at α=5.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-120-050-gn | 1,000,000 | 1 | 56.4 at α=4.75° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
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