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.

(tempest1-il) HAWKER TEMPEST 37.5% SEMISPAN AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Hawker Tempest 37.5% semispan airfoil (NPL?) Max thickness 14.5% at 38.3% chord Max camber 1% at 40.4% chord Max Cl/Cd 49.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(usa26-il) USA 26 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-26 airfoil Max thickness 9.8% at 19.9% chord Max camber 4.3% at 39.9% chord Max Cl/Cd 49.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(daytonwright6-il) Dayton-Wright 6		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dayton-Wright 6 airfoil Max thickness 13.6% at 30% chord Max camber 4.9% at 40% chord Max Cl/Cd 49.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe114-il) GOE 114 (MVA MK.1) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 114 (MVA MK.1) airfoil Max thickness 9.6% at 29.7% chord Max camber 3.5% at 49.7% chord Max Cl/Cd 49.7 at Re# 100,000 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 49.7 at Re# 100,000 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 49.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(sd7084-il) SD7084 (9.6%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD7084 low Reynolds number airfoil Max thickness 9.6% at 29.5% chord Max camber 2.3% at 38.9% chord Max Cl/Cd 49.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe498-il) GOE 498 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 498 airfoil Max thickness 15.9% at 29.4% chord Max camber 5.5% at 49.4% chord Max Cl/Cd 49.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(tsagi12-il) TSAGI 12% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	TSAGI 12% airfoil Max thickness 11.9% at 30% chord Max camber 2% at 30% chord Max Cl/Cd 49.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe447-il) GOE 447 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 447 airfoil Max thickness 12.7% at 29.7% chord Max camber 8% at 39.7% chord Max Cl/Cd 49.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database