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.

(ste87151-il) EPPLER STE 871-514 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler STE 871-514 airfoil Max thickness 13.9% at 47.3% chord Max camber 2.5% at 79% chord Max Cl/Cd 25.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(hq3015-il) HQ 3.0/15 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.0/15 R/C sailplane airfoil Max thickness 15% at 35% chord Max camber 3% at 50% chord Max Cl/Cd 25.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe758-il) GOE 758 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 758 airfoil Max thickness 13.9% at 30% chord Max camber 4.7% at 40% chord Max Cl/Cd 25.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe460-il) GOE 460 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 460 airfoil Max thickness 20.5% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 25.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(raf48-il) RAF-48 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-48 airfoil Max thickness 15% at 30% chord Max camber 2.9% at 40% chord Max Cl/Cd 25.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(nlf1015-il) NASA NLF1015		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley/Somers-Maughmer NLF(1)-1015 natural laminar flow airfoil Max thickness 15% at 39.8% chord Max camber 4.3% at 62.8% chord Max Cl/Cd 25.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e1210-il) EPPLER 1210 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E1210 general aviation airfoil Max thickness 15.9% at 21.1% chord Max camber 5.2% at 33.3% chord Max Cl/Cd 25.8 at Re# 50,000 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 25.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(tsagi-r-3a-il) TsAGI R-3a (12%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	TsAGI R-3a used on Russian ultra light aircraft (12%). Max thickness 12.1% at 23.1% chord Max camber 3.1% at 24.1% chord Max Cl/Cd 25.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(nacacyh-il) NACA CYH		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA CYH airfoil Max thickness 11.7% at 30% chord Max camber 2.8% at 40% chord Max Cl/Cd 25.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database