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.

(e668-il) EPPLER 668 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E668 sailplane airfoil Max thickness 13.9% at 37.3% chord Max camber 4% at 47.8% chord Max Cl/Cd 81.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe431-il) GOE 431 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 431 airfoil Max thickness 11.8% at 20% chord Max camber 7.2% at 60% chord Max Cl/Cd 81 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s4310-il) S4310		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4310 low Reynolds number airfoil Max thickness 10.9% at 30.7% chord Max camber 4.2% at 39.8% chord Max Cl/Cd 81 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe567-il) GOE 567 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 567 airfoil Max thickness 14.8% at 29.5% chord Max camber 5.3% at 49.5% chord Max Cl/Cd 81 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe400-il) GOE 400 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 400 airfoil Max thickness 6.1% at 20% chord Max camber 4.9% at 40% chord Max Cl/Cd 81 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(hq258-il) HQ 2.5/8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.5/8 R/C sailplane airfoil Max thickness 8% at 35% chord Max camber 2.5% at 50% chord Max Cl/Cd 80.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(clarkv-il) CLARK V AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK V airfoil Max thickness 11.6% at 30% chord Max camber 3.4% at 50% chord Max Cl/Cd 80.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s3024-il) AIRFOIL 3024 9.84%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S3024 low Reynolds number airfoil Max thickness 9.8% at 30.7% chord Max camber 3% at 44.7% chord Max Cl/Cd 80.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s4158-il) S4158		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4158 low Reynolds number airfoil Max thickness 10.9% at 35.3% chord Max camber 3.7% at 44.7% chord Max Cl/Cd 80.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(hq3510-il) HQ 3.5/10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.5/10 R/C sailplane airfoil Max thickness 10% at 35% chord Max camber 3.5% at 50% chord Max Cl/Cd 80.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database