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.

(ah21-9-il) AH21 9% version (Andrew Hollom)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Andrew Hollom AH 21 airfoil (original 9% version) Max thickness 7% at 34.9% chord Max camber 1.8% at 54.8% chord Max Cl/Cd 49 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe223-il) GOE 223 (MVA H.34) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 223 (MVA H.34) airfoil Max thickness 18.8% at 29.1% chord Max camber 5.7% at 49.1% chord Max Cl/Cd 48.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(s5020-il) S5020		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S5020 low Reynolds number airfoil Max thickness 8.4% at 27.8% chord Max camber 2.2% at 27.8% chord Max Cl/Cd 48.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe626-il) GOE 626 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 626 airfoil Max thickness 16.5% at 19.3% chord Max camber 5.1% at 49.3% chord Max Cl/Cd 48.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe797-il) GOE 797 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 797 airfoil Max thickness 16% at 30% chord Max camber 4.9% at 40% chord Max Cl/Cd 48.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(goe323-il) GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 323 (Hansa-Brandenburg V.1) airfoil Max thickness 11.1% at 29.8% chord Max camber 5.2% at 29.8% chord Max Cl/Cd 48.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe677-il) GOE 677 (= M 6) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 677 (= M 6) airfoil Max thickness 12% at 30% chord Max camber 2.2% at 30% chord Max Cl/Cd 48.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe633-il) GOE 633 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 633 airfoil Max thickness 13.8% at 19.7% chord Max camber 4% at 39.7% chord Max Cl/Cd 48.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe491-il) GOE 491 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 491 airfoil Max thickness 4.9% at 20% chord Max camber 2.9% at 30% chord Max Cl/Cd 48.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca2408-il) NACA 2408		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2408 airfoil Max thickness 8% at 29.9% chord Max camber 2% at 40% chord Max Cl/Cd 48.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database