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.

(e68-il) EPPLER 68 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E68 low Reynolds number airfoil Max thickness 13.1% at 32% chord Max camber 3.3% at 50.9% chord Max Cl/Cd 56.8 at Re# 100,000 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 56.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(stcyr24-il) St. CYR 24 (Bartel 35-IIIC)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	St. CYR 24 (Bartel 35-IIIC) airfoil Max thickness 12.4% at 30% chord Max camber 5.9% at 40% chord Max Cl/Cd 56.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(m13-il) NACA M13 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-13 airfoil Max thickness 6.2% at 30% chord Max camber 3.8% at 30% chord Max Cl/Cd 56.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(fx63145-il) FX 63-145 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 63-145 airfoil Max thickness 14.5% at 30.9% chord Max camber 4% at 37.1% chord Max Cl/Cd 56.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(goe116-il) GOE 116 (MVA MK.3) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 116 (MVA MK.3) airfoil Max thickness 9.3% at 39.8% chord Max camber 4.1% at 39.8% chord Max Cl/Cd 56.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe515-il) GOE 515 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 515 airfoil Max thickness 8.5% at 30% chord Max camber 2.8% at 40% chord Max Cl/Cd 56.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe360-il) GOE 360 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 360 airfoil Max thickness 9.7% at 29.9% chord Max camber 5.9% at 29.9% chord Max Cl/Cd 56.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe257-il) GOE 257 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 257 airfoil Max thickness 8.8% at 30% chord Max camber 4.1% at 30% chord Max Cl/Cd 56.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe280-il) GOE 280 (DAIMLER XI) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 280 (DAIMLER XI) airfoil Max thickness 7.9% at 30% chord Max camber 4.5% at 30% chord Max Cl/Cd 56.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database