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.

(goe505-il) GOE 505 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 505 airfoil Max thickness 14% at 19.7% chord Max camber 5.9% at 39.7% chord Max Cl/Cd 43.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e836-il) EPPLER E836 HYDROFOIL AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E836 hydrofoil Max thickness 12.6% at 42.8% chord Max camber 0% at 0% chord Max Cl/Cd 43.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(n5h15-il) NACA 5-H-15 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 5-H-15 rotorcraft airfoil Max thickness 15.4% at 40% chord Max camber 2.9% at 30% chord Max Cl/Cd 43.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e551-il) EPPLER 551 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E551 general aviation airfoil Max thickness 18.2% at 32.4% chord Max camber 2.8% at 57.1% chord Max Cl/Cd 43.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e297-il) EPPLER 297 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E297 tailplane airfoil Max thickness 11.4% at 37.7% chord Max camber 0% at 0% chord Max Cl/Cd 43.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(naca63206-il) NACA 63-206		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63-206 airfoil Max thickness 6% at 35% chord Max camber 1.1% at 50% chord Max Cl/Cd 43.1 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 43.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe598-il) GOE 598 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 598 airfoil Max thickness 6.5% at 39.8% chord Max camber 1% at 49.8% chord Max Cl/Cd 43.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e552-il) EPPLER 552 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E552 general aviation airfoil Max thickness 18.4% at 32.4% chord Max camber 2.6% at 51.8% chord Max Cl/Cd 43.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e521-il) EPPLER 521 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E521 tailplane airfoil Max thickness 13.8% at 37% chord Max camber 0% at 0% chord Max Cl/Cd 43.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database