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.

(m685-il) M6 (85%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M6 (85%) Max thickness 10.2% at 30% chord Max camber 1.9% at 30% chord Max Cl/Cd 66.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e748-il) EPPLER 748 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E748 sailplane airfoil Max thickness 19.7% at 27.4% chord Max camber 4.6% at 54.9% chord Max Cl/Cd 66.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e403-il) EPPLER 403 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E403 general purpose airfoil Max thickness 15% at 37.9% chord Max camber 3.2% at 75.5% chord Max Cl/Cd 66.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(geminism-il) GEMINI (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	GEMINI R/C sailplane airfoil (smoothed) Max thickness 15.4% at 34.2% chord Max camber 2.2% at 37.9% chord Max Cl/Cd 66.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(usa34-il) USA 34 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-34 airfoil Max thickness 18% at 29.5% chord Max camber 7.7% at 39.5% chord Max Cl/Cd 66.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(c141c-il) LOCKHEED C-141 BL426.57 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-141 transonic wing airfoils Max thickness 11% at 40.2% chord Max camber 1.3% at 50% chord Max Cl/Cd 66.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e662-il) EPPLER E662 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E662 sailplane airfoil Max thickness 15% at 42.8% chord Max camber 4.1% at 47.5% chord Max Cl/Cd 66.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe741-il) GOE 741 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 741 airfoil Max thickness 15.3% at 30% chord Max camber 4.8% at 30% chord Max Cl/Cd 66.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(mh23-il) MH 23 8%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 23 for F3D Pylon Racing (extended laminar flow) Max thickness 8% at 37.5% chord Max camber 1.2% at 42.7% chord Max Cl/Cd 66.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe677-il) GOE 677 (= M 6) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 677 (= M 6) airfoil Max thickness 12% at 30% chord Max camber 2.2% at 30% chord Max Cl/Cd 66.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database