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.

(ag46c03-il) AG46c -03f		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG46c -03f airfoil Max thickness 6% at 23.3% chord Max camber 1.9% at 37.3% chord Max Cl/Cd 44.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca747a415-il) NACA 747A415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 747A415 airfoil Max thickness 15% at 40.2% chord Max camber 3% at 35% chord Max Cl/Cd 44.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ag46ct02r-il) AG46ct -02f rot.		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG46ct -02f airfoil Max thickness 6.1% at 23.3% chord Max camber 1.6% at 33% chord Max Cl/Cd 44.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(c141d-il) LOCKHEED C-141 BL610.61 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Lockheed-Georgia C-141 transonic wing airfoils Max thickness 10.8% at 40.2% chord Max camber 1.5% at 50% chord Max Cl/Cd 44.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe647-il) GOE 647 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 647 airfoil Max thickness 16.2% at 19.5% chord Max camber 5.3% at 39.4% chord Max Cl/Cd 44.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(giiih-il) GIII BL207 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman/Gulfstream GIII transonic airfoils Max thickness 8.3% at 39.9% chord Max camber 1.3% at 29.9% chord Max Cl/Cd 44.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe513-il) GOE 513 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 513 airfoil Max thickness 16.6% at 29.8% chord Max camber 5.2% at 39.8% chord Max Cl/Cd 44.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(giiic-il) GIII BL75 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman/Gulfstream GIII transonic airfoils Max thickness 9.9% at 39.8% chord Max camber 0.9% at 29.8% chord Max Cl/Cd 44.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe738-il) GOE 738 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 738 airfoil Max thickness 15.4% at 30% chord Max camber 2.1% at 30% chord Max Cl/Cd 44.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe420-il) GOE 420 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 420 airfoil Max thickness 18.8% at 30% chord Max camber 4.3% at 50% chord Max Cl/Cd 44.5 at Re# 100,000 Source UIUC Airfoil Coordinates Database