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.

(c5c-il) LOCKHEED C-5A BL576 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-5A transonic wing airfoils Max thickness 11.1% at 40% chord Max camber 1.4% at 65% chord Max Cl/Cd 77.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(sc20614-il) NASA SC(2)-0614 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0614 airfoil (NASA TP-2969) Max thickness 14% at 36% chord Max camber 2.1% at 81% chord Max Cl/Cd 77.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe55-il) GOE 55 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 55 airfoil Max thickness 6.2% at 14.9% chord Max camber 2% at 19.9% chord Max Cl/Cd 77.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(e168-il) E168 (12.45%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E168 low Reynolds number airfoil Max thickness 12.4% at 26.7% chord Max camber 0% at 0% chord Max Cl/Cd 77.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(dsma523a-il) DSMA-523A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	McDonnell/Douglas DSMA-523 transonic airfoil with sharp trailing edge Max thickness 11% at 36% chord Max camber 2.3% at 82% chord Max Cl/Cd 77.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(sc20610-il) NASA SC(2)-0610 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0610 airfoil (NASA TP-2969) Max thickness 10% at 38% chord Max camber 1.8% at 82% chord Max Cl/Cd 77.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(glennmartin4-il) Glenn Martin 4		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Glenn Martin 4 airfoil Max thickness 15.5% at 30% chord Max camber 6% at 30% chord Max Cl/Cd 77.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(hq158-il) HQ 1.5/8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.5/8 R/C sailplane airfoil Max thickness 8% at 32.5% chord Max camber 1.5% at 50% chord Max Cl/Cd 77.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(npl9615-il) NPL 9615 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NPL 9615 rotorcraft airfoil Max thickness 11.3% at 34.2% chord Max camber 1% at 19.8% chord Max Cl/Cd 77.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(amsoil2-il) RUTAN WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rutan AMSOIL racer wing airfoil Max thickness 11.8% at 39% chord Max camber 1% at 48% chord Max Cl/Cd 77.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database