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.

(goe182-il) GOE 182 (MVA H.27) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 182 (MVA H.27) airfoil Max thickness 9.5% at 19.9% chord Max camber 5.3% at 39.9% chord Max Cl/Cd 36.5 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(clarkv-il) CLARK V AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK V airfoil Max thickness 11.6% at 30% chord Max camber 3.4% at 50% chord Max Cl/Cd 36.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(usa50-il) USA 50 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-50 airfoil Max thickness 7% at 30% chord Max camber 2% at 40% chord Max Cl/Cd 36.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(davis-il) Davis AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Consolidated/Davis airfoil (B-24 wing?) Max thickness 11.3% at 30% chord Max camber 3.7% at 40% chord Max Cl/Cd 36.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(hs1712-il) HAM-STD HS1-712 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	HS1 family of prop airfoils from US Patent No. 4 Max thickness 12% at 36% chord Max camber 4.9% at 44% chord Max Cl/Cd 36.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(s2062-il) S2062 8%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2062 low Reynolds number airfoil Max thickness 8% at 30.1% chord Max camber 1.5% at 49.6% chord Max Cl/Cd 36.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(ag37-il) AG37		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG37 airfoil Max thickness 7.7% at 26.5% chord Max camber 2.1% at 35.5% chord Max Cl/Cd 36.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(eiffel430-il) Eiffel 430 (Lachassgne)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eiffel 430 (Lachassgne) airfoil Max thickness 9.7% at 15% chord Max camber 4.5% at 40% chord Max Cl/Cd 36.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s2060-il) S2060 8%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S2060 low Reynolds number airfoil Max thickness 8% at 30.2% chord Max camber 1.6% at 49.7% chord Max Cl/Cd 36.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe563-il) GOE 563 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 563 airfoil Max thickness 8.9% at 29.8% chord Max camber 2.2% at 49.8% chord Max Cl/Cd 36.4 at Re# 50,000 Source UIUC Airfoil Coordinates Database