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.

(naca633218-il) NACA 63(3)-218		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(3)-218 airfoil Max thickness 18% at 34.9% chord Max camber 1.1% at 24.9% chord Max Cl/Cd 22.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e908-il) EPPLER 908 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E908 hydrofoil Max thickness 9% at 44.8% chord Max camber 2.8% at 66.3% chord Max Cl/Cd 22.2 at Re# 50,000 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 22.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca66210-il) NACA 66-210		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66-210 airfoil Max thickness 10% at 45% chord Max camber 1.1% at 50% chord Max Cl/Cd 22.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e431-il) EPPLER 431 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E431 sailplane airfoil Max thickness 15.1% at 37.4% chord Max camber 4.2% at 42.6% chord Max Cl/Cd 22.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(naca66209-il) NACA 66-209		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66-209 airfoil Max thickness 9% at 45% chord Max camber 1.1% at 50% chord Max Cl/Cd 22.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e428-il) EPPLER 428 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E428 airfoil Max thickness 11.1% at 17.2% chord Max camber 0.5% at 50.6% chord Max Cl/Cd 22.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca16012-il) NACA 16-012		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 16-012 airfoil Max thickness 12% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 22.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx74130wp2-il) 74-130 WP2		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann 74-130 WP2 airfoil Max thickness 13% at 43.5% chord Max camber 3.9% at 46.7% chord Max Cl/Cd 22.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca0018-il) NACA 0018		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0018 airfoil Max thickness 18% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 22.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database