Airfoil Tools
Search 1638 airfoils

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Your Reynold number range is 50,000 to 1,000,000. (set)

Airfoil database search

Search the 1638 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.

(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
(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

(cap21c-il) CAP 21 (TraCFoil)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CAP 21 (TraCFoil) airfoil Max thickness 15.6% at 15.7% chord Max camber 0.6% at 23.9% chord Source UIUC Airfoil Coordinates Database
(cast102-il) CAST 10-2/DOA 2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CAST 10-2/DOA 2 transonic airfoil Max thickness 12.2% at 45.4% chord Max camber 1.5% at 69.4% chord Source UIUC Airfoil Coordinates Database
(ch10sm-il) CH10 (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Chuch Hollinger CH 10-48-13 high lift low Reynolds number airfoil Max thickness 12.8% at 30.6% chord Max camber 10.2% at 49.3% chord Source UIUC Airfoil Coordinates Database
(chen-il) CHEN AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	University of Illinois at Urbana-Champaign / Chen high lift airfoil Max thickness 12.5% at 27.7% chord Max camber 7.8% at 25.4% chord Source UIUC Airfoil Coordinates Database
(clarkk-il) CLARK K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK K airfoil Max thickness 11.7% at 29.7% chord Max camber 3.3% at 39.6% chord Source UIUC Airfoil Coordinates Database