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.

(goe507-il) GOE 507 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 507 airfoil Max thickness 8.7% at 30% chord Max camber 2.9% at 40% chord Max Cl/Cd 38 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(coanda1-il) Coanda 1		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Coanda 1 airfoil Max thickness 5.7% at 30% chord Max camber 2.9% at 40% chord Max Cl/Cd 38 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(hor12-il) ONERA HOR12 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Onera propeller blade airfoils from US Patent 4 Max thickness 11.9% at 22.8% chord Max camber 3.7% at 46.2% chord Max Cl/Cd 38 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(mh122-il) MH 122 9.32%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 122 for tip section of a propeller Max thickness 9.3% at 37.6% chord Max camber 3.4% at 64.3% chord Max Cl/Cd 38 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe308-il) GOE 308 (MVA H.40) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 308 (MVA H.40) airfoil Max thickness 8.1% at 29.9% chord Max camber 5% at 29.9% chord Max Cl/Cd 37.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(goe377-il) GOE 377 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 377 airfoil Max thickness 6.5% at 30% chord Max camber 3.9% at 40% chord Max Cl/Cd 37.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(sg6043-il) SG6043		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig / Giguere SG6043 wind turbine airfoil (high L/D) Max thickness 10% at 32.1% chord Max camber 5.1% at 53.3% chord Max Cl/Cd 37.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe515-il) GOE 515 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 515 airfoil Max thickness 8.5% at 30% chord Max camber 2.8% at 40% chord Max Cl/Cd 37.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e214-il) E214 (11.1%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E214 low Reynolds number airfoil Max thickness 11.1% at 33.1% chord Max camber 3.7% at 56.9% chord Max Cl/Cd 37.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(hq2090sm-il) HQ-2.0/9 9.0% smoothed		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 2.0/9 R/C sailplane airfoil (smoothed) Max thickness 9% at 35% chord Max camber 2% at 50% chord Max Cl/Cd 37.9 at Re# 50,000 Source UIUC Airfoil Coordinates Database