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.

(usnps4-il) USNPS4 (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Jacobs USNPS4 (smoothed) 17.5 kW wind turbine airfoil Max thickness 11.9% at 34.2% chord Max camber 5% at 34.2% chord Max Cl/Cd 95.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe493-il) GOE 493 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 493 airfoil Max thickness 14.9% at 29.3% chord Max camber 3.4% at 49.3% chord Max Cl/Cd 95.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(ah94156-il) AH 94-156		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 94-156 airfoil Max thickness 15.6% at 39.6% chord Max camber 3.6% at 41.5% chord Max Cl/Cd 95.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s2027-il) S2027		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2027 low Reynolds number airfoil Max thickness 14.5% at 29.4% chord Max camber 2.7% at 38.3% chord Max Cl/Cd 95.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(mh120-il) MH 120 11.57%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 120 for tip section of a propeller Max thickness 11.6% at 34.7% chord Max camber 2.2% at 44.2% chord Max Cl/Cd 95.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(s9037-il) S9037 (9%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S9037 (9%) low Reynolds number airfoil used on the Opus R/C sailplane Max thickness 9% at 28.5% chord Max camber 3.3% at 42.4% chord Max Cl/Cd 95.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e557-il) EPPLER 557 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E557 general aviation airfoil Max thickness 16% at 30.2% chord Max camber 3.7% at 60.8% chord Max Cl/Cd 95.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe315-il) GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 315 (Hansa-Brandenburg III.5) airfoil Max thickness 8.1% at 29.9% chord Max camber 4.1% at 29.9% chord Max Cl/Cd 95.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e178-il) E178 (8.69%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E178 low Reynolds number airfoil Max thickness 8.7% at 29.8% chord Max camber 2.8% at 38.8% chord Max Cl/Cd 95.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe507-il) GOE 507 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 507 airfoil Max thickness 8.7% at 30% chord Max camber 2.9% at 40% chord Max Cl/Cd 95.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database