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.

(m4-il) NACA M4 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-4 airfoil Max thickness 6.3% at 30% chord Max camber 2.2% at 30% chord Max Cl/Cd 45.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(eh1590-il) EH 1.5/9.0		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	John Yost EH 1.5/9.0 for tailless R/C aircraft Max thickness 9% at 28.7% chord Max camber 1.5% at 25.9% chord Max Cl/Cd 45.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(rc08b3-il) NASA/LANGLEY RC-08(B)3 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley RC-08(B)3 rotorcraft airfoil Max thickness 8% at 37.8% chord Max camber 1.1% at 34.1% chord Max Cl/Cd 45.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(df102-il) DF102		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	David Fraser DF 102 low Reynolds number airfoil Max thickness 11% at 29.1% chord Max camber 2.4% at 43.5% chord Max Cl/Cd 45.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e432-il) EPPLER 432 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E432 sailplane airfoil Max thickness 16% at 37.4% chord Max camber 4.5% at 37.4% chord Max Cl/Cd 45.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(ste87391-il) EPPLER STE 87(-3)-914 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler STE 87(-3)-914 airfoil Max thickness 14.6% at 34.1% chord Max camber 4.2% at 58.3% chord Max Cl/Cd 45.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(hh02-il) HUGHES HELICOPTERS HH-02 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Hughes helicopters HH-02 rotorcraft airfoil Max thickness 9.6% at 30% chord Max camber 2% at 40% chord Max Cl/Cd 45.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(nlf0115-il) NLF(1)-0115		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley/Somers-Selig-Maughmer NLF(1)-0115 natural laminar flow airfoil Max thickness 15% at 44.1% chord Max camber 1.8% at 30% chord Max Cl/Cd 45.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ag04-il) AG04		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG04 airfoil Max thickness 6.4% at 22.5% chord Max camber 1.7% at 41.5% chord Max Cl/Cd 45.4 at Re# 100,000 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 45.4 at Re# 100,000 Source UIUC Airfoil Coordinates Database