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.

(goe456-il) GOE 456 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 456 airfoil Max thickness 7.2% at 29.9% chord Max camber 5.2% at 39.9% chord Max Cl/Cd 42.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe397-il) GOE 397 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 397 airfoil Max thickness 5.1% at 30% chord Max camber 4% at 40% chord Max Cl/Cd 42.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe346-il) GOE 346 (FRIEDRICHSHAFEN-STAAKEN) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 346 (Friedrichshafen-Staaken) airfoil Max thickness 5.7% at 39.9% chord Max camber 3.8% at 39.9% chord Max Cl/Cd 42.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe458-il) GOE 458 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 458 airfoil Max thickness 7.2% at 29.9% chord Max camber 5.2% at 39.9% chord Max Cl/Cd 42.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe483-il) GOE 483 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 483 airfoil Max thickness 5.5% at 15% chord Max camber 5.8% at 40% chord Max Cl/Cd 42.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(hs1708-il) HAM-STD HS1-708 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	HS1 family of prop airfoils from US Patent No. 4 Max thickness 7.9% at 22% chord Max camber 5% at 46% chord Max Cl/Cd 42.8 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe79-il) GOE 79 (PFALZ 11) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 79 (Pfalz 11) airfoil Max thickness 6.2% at 14.9% chord Max camber 6% at 29.9% chord Max Cl/Cd 42.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe372-il) GOE 372 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 372 airfoil Max thickness 6.2% at 29.9% chord Max camber 4.3% at 39.9% chord Max Cl/Cd 42.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe458-il) GOE 458 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 458 airfoil Max thickness 7.2% at 29.9% chord Max camber 5.2% at 39.9% chord Max Cl/Cd 42.7 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(fx60100sm-il) FX60-100 10.0% smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 60-100 airfoil (smoothed) Max thickness 10% at 27.9% chord Max camber 3.5% at 56.5% chord Max Cl/Cd 42.6 at Re# 50,000 Source UIUC Airfoil Coordinates Database