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.

(naca1412-il) NACA 1412		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 1412 airfoil Max thickness 12% at 29.9% chord Max camber 1% at 40% chord Max Cl/Cd 78.6 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(c5b-il) LOCKHEED C-5A BL488.2 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 11.5% at 40% chord Max camber 1.2% at 70% chord Max Cl/Cd 78.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(hsnlf213-il) HSNLF(1)-0213 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley HSNLF(1)-0213 high speed natural laminar flow airfoil Max thickness 13.3% at 42.4% chord Max camber 1.4% at 32.4% chord Max Cl/Cd 78.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(ht22-il) HT22		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela HT22 airfoil Max thickness 5.1% at 19.1% chord Max camber 1.1% at 22.7% chord Max Cl/Cd 78.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca1410-il) NACA 1410		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 1410 airfoil Max thickness 10% at 29.9% chord Max camber 1% at 50% chord Max Cl/Cd 78.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(nacam12-il) NACA M12		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA M12 airfoil Max thickness 11.9% at 30% chord Max camber 2% at 30% chord Max Cl/Cd 78.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(c5d-il) LOCKHEED C-5A BL758.6 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 60% chord Max Cl/Cd 78.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(n66021-il) NACA 66-021 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66(4)-021 airfoil Max thickness 21% at 45% chord Max camber 0% at 0% chord Max Cl/Cd 78.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(glennmartin3-il) Glenn Martin 3		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Glenn Martin 3 airfoil Max thickness 13.8% at 30% chord Max camber 4.6% at 30% chord Max Cl/Cd 78.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(sc20412-il) NASA SC(2)-0412 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0412 airfoil (NASA TP-2969) Max thickness 12% at 37% chord Max camber 1.3% at 83% chord Max Cl/Cd 78.2 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database