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.

(n9-il) N-9		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	N-9 airfoil Max thickness 8.5% at 30% chord Max camber 2.7% at 40% chord Max Cl/Cd 53.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe329-il) GOE 329 (PFALZ 58) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 329 (Pfalz 58) airfoil Max thickness 10.2% at 29.9% chord Max camber 5.5% at 29.9% chord Max Cl/Cd 53.3 at Re# 100,000 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 53.3 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(psu-90-125wl-il) PSU-90-125WL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	PSU-90-125WL sailplane winglet airfoil Max thickness 12.5% at 35.1% chord Max camber 2% at 54.4% chord Max Cl/Cd 53.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe622-il) GOE 622 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 622 airfoil Max thickness 8% at 30% chord Max camber 2.4% at 40% chord Max Cl/Cd 53.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(goe174-il) GOE 174 (ALBATROS 5020) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 174 (Albatros 5020) airfoil Max thickness 8.6% at 19.9% chord Max camber 5.6% at 39.9% chord Max Cl/Cd 53.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e374-il) E374		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E374 low Reynolds number airfoil Max thickness 10.9% at 34.3% chord Max camber 2% at 38.9% chord Max Cl/Cd 53.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(waspsm-il) WASP (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Mike Fox WASP low Reynolds number airfoil Max thickness 9.4% at 27.1% chord Max camber 3% at 37.9% chord Max Cl/Cd 53.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(usa40-il) USA 40 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-40 airfoil Max thickness 13.3% at 30% chord Max camber 4.2% at 40% chord Max Cl/Cd 53.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e197-il) E197 (13.49%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E197 low Reynolds number airfoil Max thickness 13.5% at 34.6% chord Max camber 2.8% at 43.7% chord Max Cl/Cd 53.2 at Re# 100,000 Source UIUC Airfoil Coordinates Database