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.

(goe366-il) GOE 366 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 366 airfoil Max thickness 13.1% at 29.8% chord Max camber 7.2% at 39.8% chord Max Cl/Cd 55 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca632615-il) NACA 63(2)-615		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(2)-615 airfoil Max thickness 15% at 34.8% chord Max camber 3.3% at 50% chord Max Cl/Cd 55 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe92-il) GOE 92 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 92 airfoil Max thickness 8.8% at 30% chord Max camber 5.5% at 30% chord Max Cl/Cd 55 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(mh201-il) MH 201 13.08%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 201 for a canard airplane (canard) Max thickness 13% at 38.1% chord Max camber 2.5% at 48.3% chord Max Cl/Cd 55 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(davis-il) Davis AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Consolidated/Davis airfoil (B-24 wing?) Max thickness 11.3% at 30% chord Max camber 3.7% at 40% chord Max Cl/Cd 55 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(e203-il) E203 (13.64%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E203 low Reynolds number airfoil Max thickness 13.6% at 30.7% chord Max camber 2.3% at 54.1% chord Max Cl/Cd 55 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e398-il) EPPLER 398 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E398 human powered aircraft airfoil Max thickness 14.2% at 29.6% chord Max camber 5.3% at 50.9% chord Max Cl/Cd 54.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e557-il) EPPLER 557 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E557 general aviation airfoil Max thickness 16% at 30.2% chord Max camber 3.7% at 60.8% chord Max Cl/Cd 54.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe515-il) GOE 515 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 515 airfoil Max thickness 8.5% at 30% chord Max camber 2.8% at 40% chord Max Cl/Cd 54.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e205-il) E205 (10.48%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E205 low Reynolds number airfoil Max thickness 10.5% at 29.7% chord Max camber 2.5% at 38.7% chord Max Cl/Cd 54.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database