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.

(goe692-il) GOE 692 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 692 airfoil Max thickness 16.1% at 30% chord Max camber 5% at 40% chord Max Cl/Cd 49.6 at Re# 100,000 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 49.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(mh42-il) MH 42 8.94%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 42 low Reynolds number airfoil Max thickness 8.9% at 31.3% chord Max camber 1.8% at 36.3% chord Max Cl/Cd 49.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(rg12a-il) AIRFOIL PROFILE12A 9.00%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rolf Girsberger RG 12A airfoil Max thickness 9% at 34.4% chord Max camber 1.8% at 34.4% chord Max Cl/Cd 49.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(df101-il) DF 101 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	David Fraser DF 101 low Reynolds number airfoil Max thickness 11% at 29.1% chord Max camber 2.3% at 43.5% chord Max Cl/Cd 49.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(goe652-il) GOE 652 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 652 airfoil Max thickness 17.1% at 20% chord Max camber 9.3% at 50% chord Max Cl/Cd 49.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(sc21010-il) NASA SC(2)-1010 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-1010 airfoil Max thickness 10% at 32% chord Max camber 2.8% at 71% chord Max Cl/Cd 49.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe324-il) GOE 324 (HANSA-BRANDENBURG) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 324 (Hansa-Brandenburg) airfoil Max thickness 13.1% at 29.8% chord Max camber 5.9% at 29.8% chord Max Cl/Cd 49.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(tsagi12-il) TSAGI 12% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	TSAGI 12% airfoil Max thickness 11.9% at 30% chord Max camber 2% at 30% chord Max Cl/Cd 49.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe227-il) GOE 227 (MVA H.37) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 227 (MVA H.37) airfoil Max thickness 14.6% at 25% chord Max camber 7.8% at 50% chord Max Cl/Cd 49.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database