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.

(ua79sfm-il) UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN ELEMENT		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	University of Alberta/Marsden UA 79-SF-187 sailplane airfoil MAIN ELEMENT Max thickness 18.8% at 42.8% chord Max camber 3% at 66.9% chord Max Cl/Cd 291 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(ua79sfm-il) UNIVERSITY OF ALBERTA UA 79-SF-187 AIRFOIL MAIN ELEMENT		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	University of Alberta/Marsden UA 79-SF-187 sailplane airfoil MAIN ELEMENT Max thickness 18.8% at 42.8% chord Max camber 3% at 66.9% chord Max Cl/Cd 241.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e58-il) EPPLER 58 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E58 low Reynolds number airfoil Max thickness 5.6% at 30% chord Max camber 6.5% at 50% chord Max Cl/Cd 235.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e63-il) E63 (4.25%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E63 low Reynolds number airfoil Max thickness 4.3% at 22.8% chord Max camber 5.3% at 50.5% chord Max Cl/Cd 235.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e61-il) E61 (5.64%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E61 low Reynolds number airfoil Max thickness 5.7% at 23.8% chord Max camber 6.4% at 51% chord Max Cl/Cd 214.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(goe804-il) GOE 804 (EA 8) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 804 (EA 8) airfoil Max thickness 6% at 40% chord Max camber 6.3% at 50% chord Max Cl/Cd 211.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e71-il) E71 (5.15%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E71 low Reynolds number airfoil Max thickness 5.2% at 25.7% chord Max camber 4.4% at 54% chord Max Cl/Cd 205 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(fx76mp120-il) FX 76-MP-120		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 76-MP-120 airfoil Max thickness 12.1% at 33.9% chord Max camber 7.6% at 46.7% chord Max Cl/Cd 192.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e62-il) E62 (5.62%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E62 low Reynolds number airfoil Max thickness 5.6% at 26.2% chord Max camber 5% at 49.3% chord Max Cl/Cd 191.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e471-il) E471 (6.25%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E471 airfoil Max thickness 6.3% at 29.8% chord Max camber 4.5% at 53.5% chord Max Cl/Cd 189.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database