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.

(fauvel-il) FAUVEL 14% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Fauvel 14% flying wing airfoil Max thickness 14% at 25.2% chord Max camber 2.5% at 25.2% chord Max Cl/Cd 18.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca000834-il) NACA 0008-34		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0008-34 airfoil Max thickness 8% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 18.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e587-il) EPPLER 587 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E587 sailplane airfoil Max thickness 16.6% at 41.1% chord Max camber 4.2% at 51.2% chord Max Cl/Cd 18.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e474-il) E474 (14.09%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E474 aerobatic aircraft airfoil Max thickness 14.1% at 21.5% chord Max camber 0% at 0% chord Max Cl/Cd 18.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(arad20-il) ARA-D 20% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Aeronautical Research Association/Bocci-Dowty Rotol ARA-D 20% thick propeller airfoil Max thickness 20% at 25% chord Max camber 3.8% at 25% chord Max Cl/Cd 18.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(ah80129-il) AH 80-129		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 80-129 airfoil Max thickness 12.9% at 40.2% chord Max camber 4.1% at 43.5% chord Max Cl/Cd 18.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(n2h15-il) NACA 2-H-15 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2-H-15 rotorcraft airfoil Max thickness 14.7% at 40% chord Max camber 4.5% at 40% chord Max Cl/Cd 18.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe476-il) GOE 476 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 476 airfoil Max thickness 14.5% at 29.5% chord Max camber 5.2% at 39.5% chord Max Cl/Cd 18.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx05191-il) WORTMANN FX 05-191 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 05-191 airfoil Max thickness 19.1% at 37.1% chord Max camber 2.6% at 50% chord Max Cl/Cd 18.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s1020-il) Ornithopter airfoil.		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1020 ornithopter airfoil Max thickness 15.1% at 33.8% chord Max camber 4.6% at 57% chord Max Cl/Cd 18.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database