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.

(goe277-il) GOE 277 (DAIMLER VIII) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 277 (DAIMLER VIII) airfoil Max thickness 8.3% at 29.9% chord Max camber 4.4% at 29.9% chord Max Cl/Cd 34 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(rg12a189-il) RG 12A-1.8/9.0 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rolf Girsberger RG 12A-1.8/9.0 airfoil Max thickness 9% at 34.4% chord Max camber 1.8% at 34.4% chord Max Cl/Cd 34 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe415-il) GOE 415 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 415 airfoil Max thickness 8.5% at 19.9% chord Max camber 3.7% at 29.9% chord Max Cl/Cd 34 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(raf26-il) RAF 26 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-26 airfoil Max thickness 6.6% at 29.9% chord Max camber 2.1% at 49.9% chord Max Cl/Cd 34 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ag455ct02r-il) AG455ct -02f rot.		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG455ct -02f airfoil Max thickness 6.5% at 23.3% chord Max camber 1.8% at 33.1% chord Max Cl/Cd 34 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(goe167-il) GOE 167 (V.KARMAN PROP.2) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 167 (V.Karman PROP.2) airfoil Max thickness 10.1% at 29.9% chord Max camber 4.5% at 29.9% chord Max Cl/Cd 34 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(mh201-il) MH 201 13.08%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 201 for a canard airplane (canard) Max thickness 13% at 38.1% chord Max camber 2.5% at 48.3% chord Max Cl/Cd 33.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e562-il) EPPLER 562 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E562 general aviation airfoil Max thickness 15% at 27.6% chord Max camber 4% at 50.8% chord Max Cl/Cd 33.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e201-il) E201 (11.88%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E201 low Reynolds number airfoil Max thickness 11.9% at 30.8% chord Max camber 2.6% at 49.4% chord Max Cl/Cd 33.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(rg14a147-il) RG 14A-1.4/7.0 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rolf Girsberger RG 14A-1.4/7.0 airfoil Max thickness 7% at 29.7% chord Max camber 1.4% at 34.3% chord Max Cl/Cd 33.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database