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.

(s1223-il) S1223		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1223 high lift low Reynolds number airfoil Max thickness 12.1% at 19.8% chord Max camber 8.1% at 49% chord Max Cl/Cd 98.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe404-il) GOE 404 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 404 airfoil Max thickness 13.2% at 29.6% chord Max camber 5% at 29.6% chord Max Cl/Cd 98.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe632-il) GOE 632 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 632 airfoil Max thickness 14% at 30% chord Max camber 3.9% at 40% chord Max Cl/Cd 98.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(jn153-il) JN-153 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Narramore JN153 airfoil Max thickness 17.6% at 28.2% chord Max camber 8.4% at 38.1% chord Max Cl/Cd 98.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe316-il) GOE 316 (HANSA-BRANDENBURG IV.5) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 316 (Hansa-Brandenburg IV.5) airfoil Max thickness 9.1% at 29.9% chord Max camber 4.2% at 29.9% chord Max Cl/Cd 98.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(boe106-il) BOEING 106 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing 106 airfoil Max thickness 13.1% at 30% chord Max camber 3.3% at 40% chord Max Cl/Cd 98.8 at Re# 500,000 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 98.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e554-il) EPPLER 554 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E554 general aviation airfoil Max thickness 18.2% at 31.8% chord Max camber 2.7% at 56.6% chord Max Cl/Cd 98.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe457-il) GOE 457 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 457 airfoil Max thickness 7.8% at 19.9% chord Max camber 4.2% at 39.9% chord Max Cl/Cd 98.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fx61163-il) FX 61-163 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 61-163 airfoil Max thickness 16.4% at 37.1% chord Max camber 2.6% at 33.9% chord Max Cl/Cd 98.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database