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.

(fx80080-il) WORTMANN FX 80-080		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 80-080 airfoil Max thickness 8.1% at 40.2% chord Max camber 2.2% at 50% chord Max Cl/Cd 90.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe438-il) GOE 438 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 438 airfoil Max thickness 11% at 29.8% chord Max camber 3.8% at 39.8% chord Max Cl/Cd 90.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe626-il) GOE 626 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 626 airfoil Max thickness 16.5% at 19.3% chord Max camber 5.1% at 49.3% chord Max Cl/Cd 90.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(mh117-il) MH 117 9.8%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 117 for a propeller for ultralight (tip) Max thickness 9.8% at 29.1% chord Max camber 2.7% at 44.6% chord Max Cl/Cd 90.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe585-il) GOE 585 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 585 airfoil Max thickness 8.2% at 20% chord Max camber 3.4% at 40% chord Max Cl/Cd 90.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(naca4415-il) NACA 4415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 4415 airfoil Max thickness 15% at 30.9% chord Max camber 4% at 40.2% chord Max Cl/Cd 90.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(usa45m-il) USA 45 M AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-45M airfoil Max thickness 11.6% at 30% chord Max camber 3.3% at 30% chord Max Cl/Cd 90.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fg3-il) Fage & Collins 3		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Fage & Collins 3 airfoil Max thickness 10.1% at 30% chord Max camber 4.3% at 30% chord Max Cl/Cd 90.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e549-il) EPPLER 549 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E549 general aviation airfoil Max thickness 18.1% at 38.7% chord Max camber 2% at 34% chord Max Cl/Cd 90.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe321-il) GOE 321 (HANSA-BRANDENBURG III.1) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 321 (Hansa-Brandenburg III.1) airfoil Max thickness 11.2% at 29.9% chord Max camber 5.1% at 29.9% chord Max Cl/Cd 90.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database