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-080-050-gn) Cambered plate C=8% T=5% R=1.6 | HAWT pipe blade with coordinates based on top surface. Camber=8% Wall thickness=5% Radius=1.603 Max thickness 8.4% at 5% chord Max camber 5.3% at 47% chord | Remove Airfoil details Airfoil plotter |
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Polars for (cp-080-050-gn)
| Plot | Airfoil | Reynolds # | Ncrit | Max Cl/Cd | Description | Source | |
|---|---|---|---|---|---|---|---|
| cp-080-050-gn | 50,000 | 9 | 25.5 at α=8.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-080-050-gn | 50,000 | 5 | 24.3 at α=9.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-080-050-gn | 50,000 | 1 | 22 at α=11° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-080-050-gn | 100,000 | 9 | 30 at α=9.75° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-080-050-gn | 100,000 | 5 | 29.3 at α=9° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-080-050-gn | 100,000 | 1 | 30.1 at α=8° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-080-050-gn | 200,000 | 9 | 33.5 at α=8° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-080-050-gn | 200,000 | 5 | 34.7 at α=9.5° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-080-050-gn | 200,000 | 1 | 37.7 at α=7.75° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-080-050-gn | 500,000 | 9 | 41.2 at α=10.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-080-050-gn | 500,000 | 5 | 44.8 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-080-050-gn | 500,000 | 1 | 51.4 at α=8° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
| cp-080-050-gn | 1,000,000 | 9 | 50.7 at α=8.25° | Mach=0 Ncrit=9 | Xfoil prediction | Details | |
| cp-080-050-gn | 1,000,000 | 5 | 57.9 at α=6.75° | Mach=0 Ncrit=5 | Xfoil prediction | Details | |
| cp-080-050-gn | 1,000,000 | 1 | 64.2 at α=8.5° | Mach=0 Ncrit=1 | Xfoil prediction | Details | |
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