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.

(goe523-il) GOE 523 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 523 airfoil Max thickness 16.5% at 29.7% chord Max camber 9.7% at 49.7% chord Max Cl/Cd 90.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe525-il) GOE 525 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 525 airfoil Max thickness 16.5% at 29.7% chord Max camber 9.7% at 49.7% chord Max Cl/Cd 90.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe243-il) GOE 243 (MVA PR.3) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 243 (MVA PR.3) airfoil Max thickness 19% at 29.3% chord Max camber 8.4% at 59.4% chord Max Cl/Cd 90.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe440-il) GOE 440 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 440 airfoil Max thickness 15.3% at 30% chord Max camber 9.7% at 40% chord Max Cl/Cd 86.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s1223rtl-il) S1223 RTL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Richard T. LaSalle modification of the S1223 to S1223RTL Max thickness 13.5% at 19.9% chord Max camber 8.3% at 55.2% chord Max Cl/Cd 85.4 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s1223rtl-il) S1223 RTL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Richard T. LaSalle modification of the S1223 to S1223RTL Max thickness 13.5% at 19.9% chord Max camber 8.3% at 55.2% chord Max Cl/Cd 84 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe572-il) GOE 572 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 572 airfoil Max thickness 18.6% at 29.9% chord Max camber 8.3% at 29.9% chord Max Cl/Cd 79.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe244-il) GOE 244 (MVA PR.4) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 244 (MVA PR.4) airfoil Max thickness 17.7% at 19.6% chord Max camber 10% at 49.6% chord Max Cl/Cd 79.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe572-il) GOE 572 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 572 airfoil Max thickness 18.6% at 29.9% chord Max camber 8.3% at 29.9% chord Max Cl/Cd 77.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(usa31-il) USA 31 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-31 airfoil Max thickness 14.8% at 19.7% chord Max camber 9.3% at 39.7% chord Max Cl/Cd 76.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database

Page 5 of 4     1 2 3 4     Next

Please see the source web site or designer for any license conditions.