Airfoil Tools
Search 1638 airfoils

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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.

(goe627-il) GOE 627 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 627 airfoil Max thickness 15.8% at 30% chord Max camber 4.1% at 30% chord Max Cl/Cd 90.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(isa960-il) I.S.A. 960		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	I.S.A. 960 airfoil Max thickness 9.5% at 30% chord Max camber 4.5% at 40% chord Max Cl/Cd 90.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(oa209-il) ONERA OA209 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale OA209 rotorcraft airfoil (Constructed from patent and smoothed) Max thickness 9% at 29.3% chord Max camber 1.6% at 17.1% chord Max Cl/Cd 90.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(b29root-il) B-29 ROOT AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing B-29 root airfoil Max thickness 22% at 30.2% chord Max camber 1.7% at 30.2% chord Max Cl/Cd 90.5 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(ncambre-il) ONERA NACA CAMBRE AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ONERA/Aerospatiale NACA-CAMBRE rotorcraft airfoil Max thickness 11.5% at 31.2% chord Max camber 1.4% at 15.9% chord Max Cl/Cd 90.4 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database

(bacxxx-il) BOEING BACXXX AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing Commercial Airplane Company BACXXX Energy Efficient Transport Program airfoil Max thickness 11.3% at 35% chord Max camber 1.4% at 15% chord Max Cl/Cd 90.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(ls421mod-il) NASA/LANGLEY LS(1)-0421MOD AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley LS(1)-0421MOD general aviation airfoil Max thickness 21% at 32.5% chord Max camber 2.3% at 30% chord Max Cl/Cd 90.3 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(du06-w-200-dt) DU 06-W-200 VAWT airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	DU 06-W-200 airfoil for Small Vertical Axis Wind Turbines (VAWT) Max thickness 19.8% at 31.1% chord Max camber 0.5% at 84.6% chord Max Cl/Cd 90.2 at Re# 1,000,000 Source TU Delft
(e221-il) E221 (9.39%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E221 low Reynolds number airfoil Max thickness 9.4% at 28.1% chord Max camber 1.6% at 32.6% chord Max Cl/Cd 90.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(ag18-il) AG18		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG18 airfoil Max thickness 5.9% at 20.7% chord Max camber 2.2% at 44.1% chord Max Cl/Cd 90.1 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database