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.

(ah79100a-il) AH 79-100 A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 79-100A airfoil Max thickness 10% at 27.9% chord Max camber 3.6% at 56.5% chord Max Cl/Cd 107.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe462-il) GOE 462 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 462 airfoil Max thickness 11% at 9.9% chord Max camber 13.4% at 29.9% chord Max Cl/Cd 107.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e337-il) EPPLER 337 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E337 flying wing airfoil Max thickness 13.1% at 32% chord Max camber 3.2% at 22.4% chord Max Cl/Cd 107.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe626-il) GOE 626 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 626 airfoil Max thickness 16.5% at 19.3% chord Max camber 5.1% at 49.3% chord Max Cl/Cd 107.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(n6h10-il) NACA 6-H-10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 6-H-10 rotorcraft airfoil Max thickness 10% at 40% chord Max camber 4.6% at 40% chord Max Cl/Cd 107.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(goe711-il) GOE 711 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 711 airfoil Max thickness 14.9% at 30% chord Max camber 6.3% at 30% chord Max Cl/Cd 107.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(sa7024-il) SA7024		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig / Ashok Gopalarathnam SA7024 low Reynolds number airfoil Max thickness 7% at 25.9% chord Max camber 3.3% at 43.3% chord Max Cl/Cd 107.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe629-il) GOE 629 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 629 airfoil Max thickness 13.6% at 29.4% chord Max camber 2.8% at 39.4% chord Max Cl/Cd 107.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(fx2-il) WORTMANN FX 2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 2 airfoil Max thickness 20.4% at 43.5% chord Max camber 3.8% at 69.1% chord Max Cl/Cd 107.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(ah79k143-il) AH 79-K-143/18		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 79-K-143/18 airfoil for use with flaps (K) Max thickness 14.3% at 40.2% chord Max camber 2.9% at 40.2% chord Max Cl/Cd 107.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database