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.

(s813-nr) NREL's S813 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S813 tip Max thickness 16% at 40.4% chord Max camber 2.3% at 54.4% chord Max Cl/Cd 130.8 at Re# 1,000,000 Source NWTC National WInd Technology Center
(goe342-il) GOE 342 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 342 airfoil Max thickness 5.4% at 20% chord Max camber 6.2% at 40% chord Max Cl/Cd 130.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(hobiesm-il) HOBIESMO1.DAT		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Hobie Hawk airfoil (Hobie Hawk R/C sailplane) Max thickness 8.6% at 25% chord Max camber 3.8% at 45% chord Max Cl/Cd 130.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e678-il) EPPLER 678 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E678 sailplane airfoil Max thickness 15.1% at 39.8% chord Max camber 5.1% at 53.7% chord Max Cl/Cd 130.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(fx6617ai-il) WORTMANN FX 66-17AII-182 AIRFOIL (AS TESTED AT NASA)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 66-17AII-182 airfoil (as tested at NASA) Max thickness 18.8% at 35.3% chord Max camber 3.7% at 40.2% chord Max Cl/Cd 130.7 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(goe359-il) GOE 359 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 359 airfoil Max thickness 7.8% at 30% chord Max camber 5.8% at 40% chord Max Cl/Cd 130.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(ah79k132-il) AH 79-K-132/20		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 79-K-132/20 airfoil for use with flaps (K) Max thickness 13.2% at 40.2% chord Max camber 3.7% at 40.2% chord Max Cl/Cd 130.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e559-il) EPPLER 559 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E559 general aviation airfoil Max thickness 16% at 27.2% chord Max camber 4.3% at 50.2% chord Max Cl/Cd 130.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe553-il) GOE 553 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 553 airfoil Max thickness 13.7% at 29.6% chord Max camber 4.7% at 39.6% chord Max Cl/Cd 130.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(sc21006-il) NASA SC(2)-1006 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-1006 airfoil Max thickness 6% at 30% chord Max camber 2.6% at 73% chord Max Cl/Cd 130.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database