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.

(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 74.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe328-il) GOE 328 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 328 airfoil Max thickness 8.2% at 30% chord Max camber 4.3% at 30% chord Max Cl/Cd 74.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e421-il) EPPLER 421 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E421 high lift airfoil Max thickness 14.5% at 26% chord Max camber 8.6% at 37.4% chord Max Cl/Cd 74.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe140-il) GOE 140 (MVA H.17) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 140 (MVA H.17) airfoil Max thickness 8.8% at 29.9% chord Max camber 5.3% at 29.9% chord Max Cl/Cd 74.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe393-il) GOE 393 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 393 airfoil Max thickness 6.1% at 19.9% chord Max camber 4.2% at 29.9% chord Max Cl/Cd 74.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(aquilasm-il) AQUILA 9.3% smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	AQUILA R/C sailplane airfoil Max thickness 9.4% at 31.3% chord Max camber 4% at 34.7% chord Max Cl/Cd 74.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(sd7037-il) SD7037-092-88		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD7037 low Reynolds number airfoil Max thickness 9.2% at 26.1% chord Max camber 2.5% at 44.7% chord Max Cl/Cd 74.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(naca652415a05-il) NACA 65(2)-415 a=0.5		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(2)-415 a=0.5 airfoil Max thickness 15% at 39.9% chord Max camber 3% at 45% chord Max Cl/Cd 74.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe177-il) GOE 177 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 177 airfoil Max thickness 7.7% at 20% chord Max camber 5% at 40% chord Max Cl/Cd 74.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx80080-il) WORTMANN FX 80-080		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 80-080 airfoil Max thickness 8.1% at 40.2% chord Max camber 2.2% at 50% chord Max Cl/Cd 74.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database