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.

(goe591-il) GOE 591 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 591 airfoil Max thickness 11.2% at 30% chord Max camber 5.1% at 40% chord Max Cl/Cd 108 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe450-il) GOE 450 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 450 airfoil Max thickness 8.9% at 29.9% chord Max camber 5.2% at 39.9% chord Max Cl/Cd 108 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s7075-il) S7075 (9%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S7075 low Reynolds number airfoil Max thickness 9% at 29% chord Max camber 2.8% at 46.8% chord Max Cl/Cd 108 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe394-il) GOE 394 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 394 airfoil Max thickness 6.1% at 19.9% chord Max camber 5.9% at 39.9% chord Max Cl/Cd 108 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe549-il) GOE 549 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 549 airfoil Max thickness 13.9% at 30% chord Max camber 4.7% at 40% chord Max Cl/Cd 107.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(goe117-il) GOE 117 (MVA MK.4) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 117 (MVA MK.4) airfoil Max thickness 9% at 29.8% chord Max camber 4.6% at 39.8% chord Max Cl/Cd 107.8 at Re# 500,000 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 107.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(usa41-il) USA 41 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-41 airfoil Max thickness 6.6% at 30% chord Max camber 4.5% at 40% chord Max Cl/Cd 107.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe364-il) GOE 364 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 364 airfoil Max thickness 10.8% at 30% chord Max camber 6.5% at 30% chord Max Cl/Cd 107.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(mh121-il) MH 121 8.76%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 121 for tip section of a propeller Max thickness 8.8% at 37.9% chord Max camber 3% at 62.2% chord Max Cl/Cd 107.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database