Airfoil Tools
Search 1638 airfoils

You have 0 airfoils loaded.
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.

(rg8-il) RG 8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rolf Girsberger RG 8 airfoil Max thickness 10.8% at 31.1% chord Max camber 2.2% at 60.5% chord Max Cl/Cd 53.7 at Re# 100,000 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 53.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe143-il) GOE 143 (MVA H.20) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 143 (MVA H.20) airfoil Max thickness 7.4% at 19.9% chord Max camber 3.8% at 29.9% chord Max Cl/Cd 53.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe590-il) GOE 590 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 590 airfoil Max thickness 5.7% at 30% chord Max camber 4% at 30% chord Max Cl/Cd 53.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe701-il) GOE 701 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 701 airfoil Max thickness 12.5% at 29.6% chord Max camber 4.9% at 39.6% chord Max Cl/Cd 53.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(s3021-il) S3021-095-84		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S3021 low Reynolds number airfoil Max thickness 9.5% at 30% chord Max camber 2.5% at 39.2% chord Max Cl/Cd 53.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe318-il) GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 318 (Hansa-Brandenburg VI.5) airfoil Max thickness 9.1% at 29.9% chord Max camber 4.3% at 29.9% chord Max Cl/Cd 53.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe322-il) GOE 322 (HANSA-BRANDENBURG IV.1) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 322 (Hansa-Brandenburg IV.1) airfoil Max thickness 13.1% at 29.8% chord Max camber 6% at 29.8% chord Max Cl/Cd 53.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe548-il) GOE 548 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 548 airfoil Max thickness 11.9% at 40% chord Max camber 2.3% at 50% chord Max Cl/Cd 53.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe187-il) GOE 187 (SCHTTE-LANZ 2U10) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 187 (Schatte-Lanz 2U10) airfoil Max thickness 8.3% at 30% chord Max camber 4.8% at 30% chord Max Cl/Cd 53.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database