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.

(e216-il) E216 (10.4%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E216 low Reynolds number airfoil Max thickness 10.4% at 26.2% chord Max camber 4.7% at 59% chord Max Cl/Cd 127.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(fx61163-il) FX 61-163 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 61-163 airfoil Max thickness 16.4% at 37.1% chord Max camber 2.6% at 33.9% chord Max Cl/Cd 127.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(lrn1007-il) lrn1007		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	LRN(1)-1007 low Reynolds number airfoil Max thickness 7.3% at 39.8% chord Max camber 5.9% at 44.6% chord Max Cl/Cd 127.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe529-il) GOE 529 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 529 airfoil Max thickness 9.7% at 29.9% chord Max camber 5.8% at 39.9% chord Max Cl/Cd 127.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(sd2083-il) SD2083 (9.0%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD2083 low Reynolds number airfoil Max thickness 9% at 35.2% chord Max camber 2.5% at 49.6% chord Max Cl/Cd 127.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(goe360-il) GOE 360 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 360 airfoil Max thickness 9.7% at 29.9% chord Max camber 5.9% at 29.9% chord Max Cl/Cd 127.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(m18-il) NACA M18 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-18 airfoil Max thickness 12% at 30% chord Max camber 4.1% at 30% chord Max Cl/Cd 127.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(raf33-il) RAF 33 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-33 airfoil Max thickness 12.6% at 30% chord Max camber 4.7% at 30% chord Max Cl/Cd 127.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe417-il) GOE 417 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 417 airfoil Max thickness 6% at 20% chord Max camber 6.1% at 40% chord Max Cl/Cd 127.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe255-il) GOE 255 (MVA CA.6) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 255 (MVA CA.6) airfoil Max thickness 18.5% at 29.1% chord Max camber 4.8% at 49.1% chord Max Cl/Cd 127.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database