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.

(r1082t-il) RONCZ 1082T VOYAGER TIP OUTER AFT WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Roncz 1082T Voyager tip outer aft wing airfoil Max thickness 16% at 40% chord Max camber 3% at 40% chord Max Cl/Cd 101.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(m15-il) NACA M15 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-15 airfoil Max thickness 12% at 30% chord Max camber 3.8% at 30% chord Max Cl/Cd 101.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe418-il) GOE 418 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 418 airfoil Max thickness 12.7% at 20% chord Max camber 5.1% at 40% chord Max Cl/Cd 101.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(strand-il) STRAND AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Strand high lift airfoil Max thickness 15.4% at 26.1% chord Max camber 4.1% at 32.1% chord Max Cl/Cd 101.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(clarkysm-il) CLARK-Y 11.7% smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK Y airfoil (smoothed) Max thickness 11.7% at 30.9% chord Max camber 3.5% at 43.5% chord Max Cl/Cd 101.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(goe330-il) GOE 330 (PFALZ 59) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 330 (Pfalz 59) airfoil Max thickness 10.2% at 29.9% chord Max camber 5.8% at 39.9% chord Max Cl/Cd 101.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe795sm-il) GOE 795 smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 795 airfoil (smoothed) Max thickness 8% at 30.9% chord Max camber 2.4% at 43.5% chord Max Cl/Cd 101.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe377-il) GOE 377 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 377 airfoil Max thickness 6.5% at 30% chord Max camber 3.9% at 40% chord Max Cl/Cd 101.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe173-il) GOE 173 (ALBATROS 6020) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 173 (Albatros 6020) airfoil Max thickness 7.8% at 20% chord Max camber 5.9% at 40% chord Max Cl/Cd 101.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe741-il) GOE 741 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 741 airfoil Max thickness 15.3% at 30% chord Max camber 4.8% at 30% chord Max Cl/Cd 101.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database