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-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 (cp-100-050-gn)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| 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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