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.

(e1200-il) EPPLER 1200 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E1200 general aviation airfoil Max thickness 16.9% at 36.1% chord Max camber 3.5% at 50.2% chord Max Cl/Cd 23.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca633018-il) NACA 63(3)-018		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(3)-018 airfoil Max thickness 18% at 33.9% chord Max camber 0% at 0% chord Max Cl/Cd 23.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(mh82-il) MH 82 13.31%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 82 for flying wings (hang glider) Max thickness 13.3% at 24.6% chord Max camber 3.9% at 24.6% chord Max Cl/Cd 23.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(rc0864c-il) NASA/LANGLEY RC08-64C AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley 08-64C rotorcraft airfoil Max thickness 8% at 40% chord Max camber 1% at 35% chord Max Cl/Cd 23.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx60160-il) FX 60-160 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 60-160 airfoil Max thickness 15.6% at 40% chord Max camber 3.1% at 60% chord Max Cl/Cd 23.4 at Re# 50,000 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 23.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca64206-il) NACA 64-206		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64-206 airfoil Max thickness 6% at 40% chord Max camber 1.1% at 50% chord Max Cl/Cd 23.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(lwk80150k25-il) LWK 80-150/K25		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	LWK 80-150/K25 symmetrical airfoil Max thickness 15% at 40.2% chord Max camber 0% at 0% chord Max Cl/Cd 23.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(nlf415-il) NASA/LANGLEY NLF(2)-0415 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley-DFVLR/Somers(NASA)-Horstmann(DFVLR) NLF(2)-0415 natural laminar flow airfoil Max thickness 15% at 47.1% chord Max camber 3% at 71.4% chord Max Cl/Cd 23.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ah81131-il) AH 81-131		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 81-131 airfoil Max thickness 13.1% at 40.2% chord Max camber 2.8% at 40.2% chord Max Cl/Cd 23.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database