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.

(e207-il) E207 (12.04%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E207 low Reynolds number airfoil Max thickness 12% at 29.6% chord Max camber 2.5% at 38.6% chord Max Cl/Cd 30.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe366-il) GOE 366 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 366 airfoil Max thickness 13.1% at 29.8% chord Max camber 7.2% at 39.8% chord Max Cl/Cd 30.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(eh2510-il) EH 2.5/10		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	John Yost EH 2.5/10 for tailless R/C aircraft Max thickness 10% at 30% chord Max camber 2.5% at 25% chord Max Cl/Cd 30.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e184-il) E184 (8.33%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E184 low Reynolds number airfoil Max thickness 8.3% at 33.3% chord Max camber 0.8% at 38.3% chord Max Cl/Cd 30.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ag46c03-il) AG46c -03f		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG46c -03f airfoil Max thickness 6% at 23.3% chord Max camber 1.9% at 37.3% chord Max Cl/Cd 30.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(eh2010-il) EH 2.0/10		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	John Yost EH 2.0/10 for tailless R/C aircraft Max thickness 10.1% at 28.7% chord Max camber 2% at 25.9% chord Max Cl/Cd 30.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ag46ct02r-il) AG46ct -02f rot.		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG46ct -02f airfoil Max thickness 6.1% at 23.3% chord Max camber 1.6% at 33% chord Max Cl/Cd 30.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(c141c-il) LOCKHEED C-141 BL426.57 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-141 transonic wing airfoils Max thickness 11% at 40.2% chord Max camber 1.3% at 50% chord Max Cl/Cd 30.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca001034a08cli02-il) NACA 0010-34 a=0.8 c(li)=0.2		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0010-34 a=0.8 c(li)=0.2 airfoil Max thickness 10% at 40% chord Max camber 1.3% at 50% chord Max Cl/Cd 30.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e210-il) E210 (13.64%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E210 low Reynolds number airfoil Max thickness 13.6% at 32.1% chord Max camber 3.7% at 50.7% chord Max Cl/Cd 30.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database