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.

(goe242-il) GOE 242 (MVA PR.2) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 242 (MVA PR.2) airfoil Max thickness 16.2% at 29.6% chord Max camber 7.5% at 49.7% chord Max Cl/Cd 78.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe155-il) GOE 155 (SSW D.1) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 155 (SSW D.1) airfoil Max thickness 7% at 29.9% chord Max camber 5.3% at 39.9% chord Max Cl/Cd 78.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe419-il) GOE 419 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 419 airfoil Max thickness 5.3% at 30% chord Max camber 4.1% at 40% chord Max Cl/Cd 78.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s4310-il) S4310		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S4310 low Reynolds number airfoil Max thickness 10.9% at 30.7% chord Max camber 4.2% at 39.8% chord Max Cl/Cd 78.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(m25-il) NACA M25 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-25 airfoil Max thickness 6.3% at 30% chord Max camber 8.2% at 30% chord Max Cl/Cd 78.5 at Re# 200,000 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 78.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(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 78.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e176-il) E176 (8.83%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E176 low Reynolds number airfoil Max thickness 8.8% at 30.5% chord Max camber 2.9% at 44.2% chord Max Cl/Cd 78.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe670-il) GOE 670 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 670 airfoil Max thickness 9% at 30% chord Max camber 3.4% at 40% chord Max Cl/Cd 78.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ah80129-il) AH 80-129		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 80-129 airfoil Max thickness 12.9% at 40.2% chord Max camber 4.1% at 43.5% chord Max Cl/Cd 78.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database