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.

(ag45ct02r-il) AG45ct -02f		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG45ct -02f airfoil Max thickness 6.9% at 23.3% chord Max camber 1.8% at 33.1% chord Max Cl/Cd 46.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe290-il) GOE 290 (MVA 290) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 290 (MVA 290) airfoil Max thickness 17.6% at 29.1% chord Max camber 3.9% at 39.2% chord Max Cl/Cd 46.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(giiij-il) GIII BL332 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman/Gulfstream GIII transonic airfoils Max thickness 8.5% at 35% chord Max camber 1.4% at 25% chord Max Cl/Cd 46.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e417-il) EPPLER 417 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E417 general purpose airfoil Max thickness 14.2% at 38.3% chord Max camber 3.1% at 76.3% chord Max Cl/Cd 46.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(supermarine371i-il) Supermarine 371-I (root)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Supermarine 371-I root airfoil Max thickness 13% at 40% chord Max camber 0.9% at 50% chord Max Cl/Cd 46.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(naca651212-il) NACA 65(1)-212		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(1)-212 airfoil Max thickness 12% at 40% chord Max camber 1.1% at 50% chord Max Cl/Cd 46.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(avistar-il) AVISTAR		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Hobbico R/C Avistar trainer airfoil Max thickness 14.5% at 34.2% chord Max camber 2.3% at 37.9% chord Max Cl/Cd 46.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca25112-jf) NACA 25112		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	NACA 25112 5 digit reflex airfoil Max thickness 12% at 29.5% chord Max camber 2% at 27.2% chord Max Cl/Cd 46.7 at Re# 100,000 Source Javafoil generated
(e422-il) EPPLER 422 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E422 high lift airfoil Max thickness 14% at 24.1% chord Max camber 7.1% at 34.8% chord Max Cl/Cd 46.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca651212a06-il) NACA 65(1)-212 a=0.6		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(1)-212 a=0.6 airfoil Max thickness 12% at 40% chord Max camber 1.5% at 50% chord Max Cl/Cd 46.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database