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.

(tsagi12-il) TSAGI 12% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	TSAGI 12% airfoil Max thickness 11.9% at 30% chord Max camber 2% at 30% chord Max Cl/Cd 66.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(naca2408-il) NACA 2408		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2408 airfoil Max thickness 8% at 29.9% chord Max camber 2% at 40% chord Max Cl/Cd 66.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe422-il) GOE 422 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 422 airfoil Max thickness 17.1% at 29.5% chord Max camber 6.5% at 39.5% chord Max Cl/Cd 66.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(usa35a-il) USA 35 A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-35A airfoil Max thickness 18.2% at 29.4% chord Max camber 6.4% at 39.4% chord Max Cl/Cd 66.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(sc21006-il) NASA SC(2)-1006 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-1006 airfoil Max thickness 6% at 30% chord Max camber 2.6% at 73% chord Max Cl/Cd 66.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(hq17-il) HORSTMANN AND QUAST HQ-17/14.38 AIRFOIL (MEASURED)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Airfoil measured from an ASW22 wing Max thickness 15.2% at 42% chord Max camber 4.5% at 42% chord Max Cl/Cd 66.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(usa35-il) USA 35 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-35 airfoil Max thickness 18.2% at 29.4% chord Max camber 6.4% at 39.4% chord Max Cl/Cd 66.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(m6-il) NACA M6 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-6 airfoil Max thickness 12% at 30% chord Max camber 2.2% at 30% chord Max Cl/Cd 66.5 at Re# 200,000 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 66.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ag24-il) AG24 Bubble Dancer DLG by Mark Drela		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG24 airfoil used on the Bubble Dancer R/C DLG Max thickness 8.4% at 26% chord Max camber 2.2% at 46.9% chord Max Cl/Cd 66.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database