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.

(naca644221-il) NACA 64(4)-221		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(4)-221 airfoil Max thickness 21% at 34.9% chord Max camber 1.1% at 50% chord Max Cl/Cd 90.7 at Re# 500,000 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 90.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(hq2012-il) HQ 2.0/12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.0/12 R/C sailplane airfoil Max thickness 12% at 35% chord Max camber 2% at 50% chord Max Cl/Cd 90.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(hq3518-il) HQ 3.5/18 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.5/18 R/C sailplane airfoil Max thickness 18% at 35% chord Max camber 3.5% at 50% chord Max Cl/Cd 90.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe309-il) GOE 309 (MVA H.41) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 309 (MVA H.41) airfoil Max thickness 8.4% at 30% chord Max camber 4.7% at 30% chord Max Cl/Cd 90.6 at Re# 500,000 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 90.6 at Re# 500,000 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 90.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe365-il) GOE 365 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 365 airfoil Max thickness 11.7% at 29.9% chord Max camber 5.1% at 39.9% chord Max Cl/Cd 90.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(raf28-il) RAF 28 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-28 airfoil Max thickness 9.8% at 30% chord Max camber 1.9% at 40% chord Max Cl/Cd 90.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(hq3512-il) HQ 3.5/12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.5/12 R/C sailplane airfoil Max thickness 12% at 35% chord Max camber 3.5% at 50% chord Max Cl/Cd 90.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database