Airfoil Tools
Search 1638 airfoils

You have 0 airfoils loaded.
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.

(e603-il) EPPLER 603 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E603 general purpose airfoil Max thickness 19% at 40% chord Max camber 3.6% at 35.6% chord Max Cl/Cd 63 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e421-il) EPPLER 421 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E421 high lift airfoil Max thickness 14.5% at 26% chord Max camber 8.6% at 37.4% chord Max Cl/Cd 63 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(naca634421-il) NACA 63(4)-421		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(4)-421 airfoil Max thickness 21% at 34.8% chord Max camber 2.2% at 50% chord Max Cl/Cd 63 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe390-il) GOE 390 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 390 airfoil Max thickness 20.3% at 29.2% chord Max camber 6.9% at 39.2% chord Max Cl/Cd 62.9 at Re# 200,000 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 62.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(goe375-il) GOE 375 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 375 airfoil Max thickness 6.5% at 20% chord Max camber 4.5% at 30% chord Max Cl/Cd 62.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(rc10b3-il) NASA/LANGLEY RC-10(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-10(B)3 rotorcraft airfoil Max thickness 10% at 37.7% chord Max camber 1.7% at 30.3% chord Max Cl/Cd 62.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(usa27m2-il) USA 27 mod. AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-27MOD airfoil Max thickness 13.3% at 30% chord Max camber 5% at 40% chord Max Cl/Cd 62.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe587-il) GOE 587 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 587 airfoil Max thickness 5.8% at 40% chord Max camber 3% at 30% chord Max Cl/Cd 62.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s2060-il) S2060 8%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2060 low Reynolds number airfoil Max thickness 8% at 30.2% chord Max camber 1.6% at 49.7% chord Max Cl/Cd 62.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database