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.

(eh2012-il) EH 2.0/12		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	John Yost EH 2.0/12 for tailless R/C aircraft Max thickness 12% at 28.7% chord Max camber 2% at 25.9% chord Max Cl/Cd 61.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(raf19-il) RAF 19 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-19 airfoil Max thickness 10.5% at 15% chord Max camber 10.1% at 40% chord Max Cl/Cd 61.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e548-il) EPPLER 548 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E548 general aviation airfoil Max thickness 17.4% at 35.4% chord Max camber 2.2% at 26.1% chord Max Cl/Cd 61.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s8036-il) S8036 (16%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S8036 low Reynolds number airfoil Max thickness 16% at 36.8% chord Max camber 1.3% at 40.4% chord Max Cl/Cd 61.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e544-il) EPPLER 544 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E544 general aviation airfoil Max thickness 17.5% at 40% chord Max camber 1.9% at 30.5% chord Max Cl/Cd 61.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(hq159-il) HQ 1.5/9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.5/9 R/C sailplane airfoil Max thickness 9% at 35% chord Max camber 1.5% at 50% chord Max Cl/Cd 61.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ls417-il) NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley/Whitcomb LS(1)-0417 (GA(W)-1) general aviation airfoil Max thickness 17% at 40% chord Max camber 2.4% at 65% chord Max Cl/Cd 61.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e636-il) EPPLER 636 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E636 airfoil Max thickness 11.9% at 26.9% chord Max camber 3.2% at 22.9% chord Max Cl/Cd 61.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe798-il) GOE 798 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 798 airfoil Max thickness 20% at 30% chord Max camber 6% at 40% chord Max Cl/Cd 61.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe386-il) GOE 386 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 386 airfoil Max thickness 20.3% at 29% chord Max camber 5.4% at 39% chord Max Cl/Cd 61.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database