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-060-050-gn) Cambered plate C=6% T=5% R=2.11 | HAWT pipe blade with coordinates based on top surface. Camber=6% Wall thickness=5% Radius=2.113 Max thickness 10.8% at 6.3% chord Max camber 2.7% at 52.1% chord | Remove Airfoil details Airfoil plotter |
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Polars for (cp-060-050-gn)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| cp-060-050-gn | 50,000 | 9 | 19.6 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-060-050-gn | 50,000 | 5 | 20.1 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-060-050-gn | 50,000 | 1 | 21.2 at α=11° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-060-050-gn | 100,000 | 9 | 22.4 at α=7.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-060-050-gn | 100,000 | 5 | 25 at α=8.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-060-050-gn | 100,000 | 1 | 28 at α=10° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-060-050-gn | 200,000 | 9 | 26.1 at α=7.5° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-060-050-gn | 200,000 | 5 | 31.4 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-060-050-gn | 200,000 | 1 | 35.7 at α=10.5° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-060-050-gn | 500,000 | 9 | 35.9 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-060-050-gn | 500,000 | 5 | 45.2 at α=12.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-060-050-gn | 500,000 | 1 | 50 at α=11° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-060-050-gn | 1,000,000 | 9 | 51.4 at α=12° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-060-050-gn | 1,000,000 | 5 | 60.1 at α=13° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-060-050-gn | 1,000,000 | 1 | 64.2 at α=11.5° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
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