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.

(defcnd2-il) DEFIANT CANARD BL110 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rutan DEFIANT canard BL110 airfoil Max thickness 14.7% at 28.6% chord Max camber 3.8% at 28.6% chord Max Cl/Cd 89.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(defcnd2-il) DEFIANT CANARD BL110 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rutan DEFIANT canard BL110 airfoil Max thickness 14.7% at 28.6% chord Max camber 3.8% at 28.6% chord Max Cl/Cd 89.6 at Re# 500,000 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 89.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(daytonwright6-il) Dayton-Wright 6		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dayton-Wright 6 airfoil Max thickness 13.6% at 30% chord Max camber 4.9% at 40% chord Max Cl/Cd 89.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e1211-il) EPPLER 1211 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E1211 general aviation airfoil Max thickness 18% at 20.9% chord Max camber 4.4% at 37.7% chord Max Cl/Cd 89.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(goe530-il) GOE 530 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 530 airfoil Max thickness 12.9% at 29.8% chord Max camber 5.1% at 29.8% chord Max Cl/Cd 89.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca643218-il) NACA 64(3)-218		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(3)-218 airfoil Max thickness 18% at 34.9% chord Max camber 1.1% at 50% chord Max Cl/Cd 89.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(ls421-il) NASA/LANGLEY LS(1)-0421 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley LS(1)-0421 general aviation airfoil Max thickness 20.9% at 40% chord Max camber 2.4% at 65% chord Max Cl/Cd 89.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe363-il) GOE 363 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 363 airfoil Max thickness 11.1% at 19.8% chord Max camber 5.7% at 39.8% chord Max Cl/Cd 89.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe655-il) GOE 655 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 655 airfoil Max thickness 13.9% at 30% chord Max camber 4.4% at 40% chord Max Cl/Cd 89.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database