Airfoil database search
Search the 1636 airfoils available in the databases filtering by name, thickness and camber. Click on an airfoil image to display a larger preview picture. There are links to the original airfoil source and dat file and the details page with polar diagrams for a range of Reynolds numbers.
(du06-w-200-dt) DU 06-W-200 VAWT airfoil | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file | |
 | DU 06-W-200 airfoil for Small Vertical Axis Wind Turbines (VAWT) Max thickness 19.8% at 31.1% chord Max camber 0.5% at 84.6% chord Source TU Delft | |
(cp-060-050-gn) Cambered plate C=6% T=5% R=2.11 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file | |
 | 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 Source Generated | |
(cp-080-050-gn) Cambered plate C=8% T=5% R=1.6 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file | |
 | 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 Source Generated | |
(cp-100-050-gn) Cambered plate C=10% T=5% R=1.3 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file | |
 | 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 Source Generated | |
(cp-120-050-gn) Cambered plate C=12% T=5% R=1.1 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file | |
 | 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 Source Generated | |
(cp-140-050-gn) Cambered plate C=14% T=5% R=0.96 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file | |
 | HAWT pipe blade with coordinates based on top surface. Camber=14% Wall thickness=5% Radius=0.963 Max thickness 5.5% at 3.6% chord Max camber 12.2% at 47.7% chord Source Generated | |
(cp-160-050-gn) Cambered plate C=16% T=5% R=0.86 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file | |
 | 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 Source Generated | |
(cp-180-050-gn) Cambered plate C=18% T=5% R=0.78 | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file | |
 | HAWT pipe blade with coordinates based on top surface. Camber=18% Wall thickness=5% Radius=0.784 Max thickness 5% at 3.2% chord Max camber 16.4% at 49.3% chord Source Generated | |
(joukowsk0009-jf) Joukovsky f=0% t=9% | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file | |
 | Joukowski 9% symmetrical airfoil Max thickness 9% at 25.5% chord Max camber 0% at 0% chord Source Javafoil generated | |
(joukowsk0015-jf) Joukovsky f=0% t=15% | Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file | |
 | Joukowski 15% symmetrical airfoil Max thickness 15% at 24.6% chord Max camber 0% at 0% chord Source Javafoil generated | |
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