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.

(rg149-il) RG 14 9% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rolf Girsberger RG 14 (9%) airfoil Max thickness 9% at 31% chord Max camber 1.6% at 36% chord Max Cl/Cd 46.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(eh2070-il) EH 2.0/7.0		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	John Yost EH 2.0/7.0 for tailless R/C aircraft Max thickness 7% at 28.7% chord Max camber 2% at 25.9% chord Max Cl/Cd 46.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe375-il) GOE 375 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 375 airfoil Max thickness 6.5% at 20% chord Max camber 4.5% at 30% chord Max Cl/Cd 46.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fx082512-il) WORTMANN FX 082-512 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 082-512 airfoil Max thickness 11.8% at 25% chord Max camber 4.2% at 62.9% chord Max Cl/Cd 46.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(rc510-il) NASA RC(5)-10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley RC(5)-10 rotorcraft airfoil Max thickness 10% at 40.1% chord Max camber 2.2% at 25.3% chord Max Cl/Cd 46.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(n2415-il) NACA 2415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2415 airfoil Max thickness 15% at 29.5% chord Max camber 2% at 39.6% chord Max Cl/Cd 46.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca652415-il) NACA 65(2)-415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(2)-415 airfoil Max thickness 15% at 39.9% chord Max camber 2.2% at 50% chord Max Cl/Cd 46.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe15-il) GOE 15 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 15 airfoil Max thickness 9% at 29.8% chord Max camber 7.8% at 29.8% chord Max Cl/Cd 46.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(mh60-il) MH 60 10.08%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 60 for flying wings Max thickness 10.1% at 26.9% chord Max camber 1.7% at 36.6% chord Max Cl/Cd 46.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe528-il) GOE 528 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 528 airfoil Max thickness 12.5% at 29.8% chord Max camber 6.2% at 39.8% chord Max Cl/Cd 46.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database