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.

(clarkk-il) CLARK K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK K airfoil Max thickness 11.7% at 29.7% chord Max camber 3.3% at 39.6% chord Max Cl/Cd 71.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe177-il) GOE 177 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 177 airfoil Max thickness 7.7% at 20% chord Max camber 5% at 40% chord Max Cl/Cd 71.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(n6h10-il) NACA 6-H-10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 6-H-10 rotorcraft airfoil Max thickness 10% at 40% chord Max camber 4.6% at 40% chord Max Cl/Cd 71.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe523-il) GOE 523 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 523 airfoil Max thickness 16.5% at 29.7% chord Max camber 9.7% at 49.7% chord Max Cl/Cd 71.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe525-il) GOE 525 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 525 airfoil Max thickness 16.5% at 29.7% chord Max camber 9.7% at 49.7% chord Max Cl/Cd 71.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(fx66a175-il) WORTMANN FX 66-17A-175 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 66-17A-175 airfoil Max thickness 17.5% at 33.9% chord Max camber 4.2% at 40.2% chord Max Cl/Cd 71.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(raf38-il) RAF 38 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-38 airfoil Max thickness 12.7% at 30% chord Max camber 2.5% at 40% chord Max Cl/Cd 71.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e654-il) EPPLER 654 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E654 sailplane airfoil Max thickness 17.2% at 36.1% chord Max camber 4.9% at 46.5% chord Max Cl/Cd 71.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(daytonwrightt1-il) Dayton-Wright T-1		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dayton-Wright T-1 airfoil Max thickness 13.4% at 30% chord Max camber 4.4% at 40% chord Max Cl/Cd 71.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(kc135c-il) KC-135 BL200.76 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing KC-135 transonic airfoils Max thickness 10.6% at 40% chord Max camber 1.5% at 25% chord Max Cl/Cd 71.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database