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.

(m16-il) NACA M16 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-16 airfoil Max thickness 6.2% at 30% chord Max camber 4.1% at 30% chord Max Cl/Cd 53.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ag25-il) AG25 Bubble Dancer DLG by Mark Drela		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG25 airfoil used on the Bubble Dancer R/C DLG Max thickness 7.6% at 24.7% chord Max camber 2.4% at 45.4% chord Max Cl/Cd 53.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(du84132v-il) DELFT DU84-132V3 AIRFOIL (MEASURED)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Airfoil measured from an ASW22 wing Max thickness 13.6% at 33.9% chord Max camber 3.1% at 45.3% chord Max Cl/Cd 53.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s2060-il) S2060 8%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2060 low Reynolds number airfoil Max thickness 8% at 30.2% chord Max camber 1.6% at 49.7% chord Max Cl/Cd 53.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fg2-il) Fage & Collins 2		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Fage & Collins 2 airfoil Max thickness 8.2% at 30% chord Max camber 3.3% at 30% chord Max Cl/Cd 53.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(goe415-il) GOE 415 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 415 airfoil Max thickness 8.5% at 19.9% chord Max camber 3.7% at 29.9% chord Max Cl/Cd 53.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(mh121-il) MH 121 8.76%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 121 for tip section of a propeller Max thickness 8.8% at 37.9% chord Max camber 3% at 62.2% chord Max Cl/Cd 53.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(m16-il) NACA M16 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-16 airfoil Max thickness 6.2% at 30% chord Max camber 4.1% at 30% chord Max Cl/Cd 53.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe507-il) GOE 507 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 507 airfoil Max thickness 8.7% at 30% chord Max camber 2.9% at 40% chord Max Cl/Cd 53.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe795-il) GOE 795 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 795 airfoil Max thickness 8% at 30.9% chord Max camber 2.4% at 43.5% chord Max Cl/Cd 53.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database