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.

(s4110-il) S4110		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4110 low Reynolds number airfoil Max thickness 8.4% at 26.6% chord Max camber 3.1% at 45.4% chord Max Cl/Cd 73.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(clarkw-il) CLARK W AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK W airfoil Max thickness 11.2% at 30% chord Max camber 3.7% at 40% chord Max Cl/Cd 73.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(usa22-il) USA 22 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-22 airfoil Max thickness 9.1% at 19.9% chord Max camber 4.4% at 39.9% chord Max Cl/Cd 73.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ah21-9-il) AH21 9% version (Andrew Hollom)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Andrew Hollom AH 21 airfoil (original 9% version) Max thickness 7% at 34.9% chord Max camber 1.8% at 54.8% chord Max Cl/Cd 73.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe277-il) GOE 277 (DAIMLER VIII) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 277 (DAIMLER VIII) airfoil Max thickness 8.3% at 29.9% chord Max camber 4.4% at 29.9% chord Max Cl/Cd 73.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(e178-il) E178 (8.69%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E178 low Reynolds number airfoil Max thickness 8.7% at 29.8% chord Max camber 2.8% at 38.8% chord Max Cl/Cd 73.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe630-il) GOE 630 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 630 airfoil Max thickness 12.6% at 29.8% chord Max camber 7.7% at 39.8% chord Max Cl/Cd 73.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe279-il) GOE 279 (DAIMLER X) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 279 (DAIMLER X) airfoil Max thickness 7.4% at 30% chord Max camber 4.7% at 40% chord Max Cl/Cd 73.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(hq300gd2-il) HORSTMANN AND QUAST HQ-300 GD(MOD 2) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	DFVLR/Braunschweig Horstmann and Quast HQ-300 GD(MOD 2) sailplane airfoil Max thickness 16.6% at 39.1% chord Max camber 3.9% at 39.1% chord Max Cl/Cd 73.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ah93k130-il) AH 93-K-130/15		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-K-130/15 airfoil for use with flaps (K) Max thickness 13.1% at 42% chord Max camber 3.5% at 42% chord Max Cl/Cd 73.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database