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.

(oaf117-il) OAF117 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OAF117 Fenestron airfoil Max thickness 11.5% at 23.2% chord Max camber 2% at 46.9% chord Max Cl/Cd 78.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(mh110-il) MH 110 10.01%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 110 for stall controlled wind turbines (tip) Max thickness 10% at 23.9% chord Max camber 1% at 15.8% chord Max Cl/Cd 78.5 at Re# 500,000 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 78.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(ah21-9-il) AH21 9% version (Andrew Hollom)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Andrew Hollom AH 21 airfoil (original 9% version) Max thickness 7% at 34.9% chord Max camber 1.8% at 54.8% chord Max Cl/Cd 78.4 at Re# 500,000 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 78.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(bacnlf-il) BOEING HSNLF AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing high speed natural laminar flow airfoil from a European patent (EP 0111785A1) Max thickness 10.1% at 43.7% chord Max camber 1.3% at 76.7% chord Max Cl/Cd 78.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe384-il) GOE 384 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 384 airfoil Max thickness 19.6% at 29.3% chord Max camber 6.9% at 39.3% chord Max Cl/Cd 78.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e541-il) EPPLER 541 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E541 general aviation airfoil Max thickness 16.6% at 46.2% chord Max camber 1.7% at 36.3% chord Max Cl/Cd 78.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e1214-il) EPPLER 1214 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E1214 general aviation airfoil Max thickness 19.8% at 26.2% chord Max camber 2.1% at 30.4% chord Max Cl/Cd 78.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(sd7090-il) SD7090 (10%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD7090 low Reynolds number airfoil Max thickness 10% at 29.3% chord Max camber 1.5% at 43.6% chord Max Cl/Cd 78.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database