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.

(rc1064c-il) NASA/LANGLEY RC10-64C AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley 10-64C rotorcraft airfoil Max thickness 10% at 40% chord Max camber 1% at 35% chord Max Cl/Cd 31.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s801-nr) NREL's S801 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S801 primary 13.5% Not recommended Max thickness 13.5% at 37.8% chord Max camber 3.7% at 47.1% chord Max Cl/Cd 31.7 at Re# 50,000 Source NWTC National WInd Technology Center
(vr5-il) BOEING-VERTOL VR-5 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol VR-5 rotorcraft airfoil Max thickness 12% at 35% chord Max camber 3.4% at 35% chord Max Cl/Cd 31.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe598-il) GOE 598 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 598 airfoil Max thickness 6.5% at 39.8% chord Max camber 1% at 49.8% chord Max Cl/Cd 31.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(glennmartin2-il) Glenn Martin 2		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Glenn Martin 2 airfoil Max thickness 13.5% at 20% chord Max camber 6.1% at 30% chord Max Cl/Cd 31.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(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 31.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe188-il) GOE 188 (SCHTTE-LANZ 3U10) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 188 (Schatte-Lanz 3U10) airfoil Max thickness 8.9% at 30% chord Max camber 4.3% at 30% chord Max Cl/Cd 31.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(eiffel371-il) Eiffel 371 (Monge)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eiffel 371 (Monge) airfoil Max thickness 14.4% at 30% chord Max camber 3.3% at 30% chord Max Cl/Cd 31.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(oa212-il) ONERA OA212 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OA212 rotorcraft airfoil (Constructed from patent and smoothed) Max thickness 12% at 31.8% chord Max camber 2.3% at 31.8% chord Max Cl/Cd 31.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fxm2-il) WORTMANN FX M2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX M2 airfoil Max thickness 8.4% at 19.6% chord Max camber 4.8% at 30.9% chord Max Cl/Cd 31.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database