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.

(e220-il) E220 (11.48%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E220 low Reynolds number airfoil Max thickness 11.5% at 33.1% chord Max camber 2.2% at 37.7% chord Max Cl/Cd 97.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(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 Max Cl/Cd 97.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(ah93w215-il) AH 93-W-215		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-W-215 airfoil for use on wind turbines (W) Max thickness 21.2% at 33.9% chord Max camber 3.1% at 40.2% chord Max Cl/Cd 97.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe735-il) GOE 735 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 735 airfoil Max thickness 20.1% at 30% chord Max camber 4.4% at 30% chord Max Cl/Cd 97.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(s9000-il) S9000 (9%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S9000 (9%) low Reynolds number airfoil used on the Blackhawk R/C sailplane Max thickness 9% at 28.2% chord Max camber 2.1% at 44.8% chord Max Cl/Cd 97.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(fx63147-il) FX 63-147 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 63-147 airfoil Max thickness 14.7% at 33.9% chord Max camber 3.1% at 33.9% chord Max Cl/Cd 97.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe122-il) GOE 122 (MVA H.2) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 122 (MVA H.2) airfoil Max thickness 7.3% at 30% chord Max camber 4.1% at 30% chord Max Cl/Cd 97.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe693-il) GOE 693 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 693 airfoil Max thickness 12% at 30% chord Max camber 3.6% at 40% chord Max Cl/Cd 97.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(usa46-il) USA 46 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-46 airfoil Max thickness 6.5% at 20% chord Max camber 2.2% at 40% chord Max Cl/Cd 97.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(ag44ct02r-il) AG44ct -02f		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG44ct -02f airfoil Max thickness 7.3% at 24.6% chord Max camber 1.9% at 34.4% chord Max Cl/Cd 97.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database