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-160-050-gn) Cambered plate C=16% T=5% R=0.86 | HAWT pipe blade with coordinates based on top surface. Camber=16% Wall thickness=5% Radius=0.861 Max thickness 5.2% at 3.4% chord Max camber 14.3% at 49.2% chord | Remove Airfoil details Airfoil plotter |
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Polars for (cp-160-050-gn)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| cp-160-050-gn | 50,000 | 9 | 16.5 at α=15.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-160-050-gn | 50,000 | 5 | 15.1 at α=16.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-160-050-gn | 50,000 | 1 | 13.1 at α=9.25° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-160-050-gn | 100,000 | 9 | 21 at α=9° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-160-050-gn | 100,000 | 5 | 20.1 at α=8.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-160-050-gn | 100,000 | 1 | 21 at α=6.75° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-160-050-gn | 200,000 | 9 | 39.1 at α=6.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-160-050-gn | 200,000 | 5 | 37.9 at α=5.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-160-050-gn | 200,000 | 1 | 34.2 at α=4.25° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-160-050-gn | 500,000 | 9 | 58.3 at α=3.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-160-050-gn | 500,000 | 5 | 49.2 at α=3.25° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-160-050-gn | 500,000 | 1 | 33.3 at α=2.25° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-160-050-gn | 1,000,000 | 9 | 56 at α=3° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-160-050-gn | 1,000,000 | 5 | 48.9 at α=2.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-160-050-gn | 1,000,000 | 1 | 33.7 at α=7° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
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