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.

(ls413-il) NASA/LANGLEY LS(1)-0413 (GA(W)-2) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley LS(1)-0413 (GA(W)-2) general aviation airfoil Max thickness 12.9% at 37.5% chord Max camber 2.4% at 65% chord Max Cl/Cd 82.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fx75vg166-il) FX 75-VG-166/22		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 75-VG-166/22 variable geometry airfoil Max thickness 16.7% at 43.5% chord Max camber 2.4% at 40.2% chord Max Cl/Cd 82.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe05k-il) GOE 5K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 5K airfoil Max thickness 3.7% at 50% chord Max camber 1.5% at 50% chord Max Cl/Cd 82.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(ag16-il) AG16		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG16 airfoil Max thickness 7.1% at 23.4% chord Max camber 1.9% at 46.9% chord Max Cl/Cd 82.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe510-il) GOE 510 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 510 airfoil Max thickness 13.7% at 19.7% chord Max camber 5.8% at 39.7% chord Max Cl/Cd 82.4 at Re# 500,000 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 82.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca644221-il) NACA 64(4)-221		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(4)-221 airfoil Max thickness 21% at 34.9% chord Max camber 1.1% at 50% chord Max Cl/Cd 82.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(arad10-il) ARA-D 10% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Aeronautical Research Association/Bocci-Dowty Rotol ARA-D 10% thick propeller airfoil Max thickness 10% at 25% chord Max camber 4% at 35% chord Max Cl/Cd 82.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s102s-il) SOMERS S102 AIRFOIL (SHARP)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dan Somers airfoil for the Toyota general aviation airplane Max thickness 15% at 40% chord Max camber 2.1% at 68.7% chord Max Cl/Cd 82.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e180-il) E180 (8.59%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E180 low Reynolds number airfoil Max thickness 8.6% at 33.5% chord Max camber 2% at 38.1% chord Max Cl/Cd 82.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database