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.

(goe442-il) GOE 442 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 442 airfoil Max thickness 7.7% at 19.9% chord Max camber 4.3% at 39.9% chord Max Cl/Cd 73.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe389-il) GOE 389 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 389 airfoil Max thickness 10.3% at 29.8% chord Max camber 4% at 39.8% chord Max Cl/Cd 73.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ah93k132-il) AH 93-K-132/15		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-K-132/15 airfoil for use with flaps (K) Max thickness 13.2% at 41.2% chord Max camber 3.5% at 41.2% chord Max Cl/Cd 73.4 at Re# 200,000 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 73.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe325-il) GOE 325 (PFALZ 54) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 325 (Pfalz 54) airfoil Max thickness 8.2% at 20% chord Max camber 4.6% at 30% chord Max Cl/Cd 73.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(naca633618-il) NACA 63(3)-618		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(3)-618 airfoil Max thickness 18% at 34.7% chord Max camber 3.3% at 50% chord Max Cl/Cd 73.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe673-il) GOE 673 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 673 airfoil Max thickness 10.8% at 29.7% chord Max camber 2.8% at 49.7% chord Max Cl/Cd 73.4 at Re# 200,000 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 73.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe802b-il) GOE 802 B AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 802 B airfoil Max thickness 9.8% at 30% chord Max camber 6.1% at 40% chord Max Cl/Cd 73.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ah82150a-il) AH 82-150 A		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 82-150 A airfoil Max thickness 15% at 40.2% chord Max camber 3.3% at 43.5% chord Max Cl/Cd 73.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database