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.

(e203-il) E203 (13.64%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E203 low Reynolds number airfoil Max thickness 13.6% at 30.7% chord Max camber 2.3% at 54.1% chord Max Cl/Cd 101.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe478-il) GOE 478 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 478 airfoil Max thickness 13.4% at 29.6% chord Max camber 4.3% at 39.6% chord Max Cl/Cd 101.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fx61168-il) FX 61-168 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 61-168 airfoil Max thickness 16.8% at 37.1% chord Max camber 3% at 37.1% chord Max Cl/Cd 101.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe281-il) GOE 281 (DAIMLER XII) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 281 (DAIMLER XII) airfoil Max thickness 8% at 30% chord Max camber 4.5% at 40% chord Max Cl/Cd 101.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe423-il) GOE 423 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 423 airfoil Max thickness 16.9% at 39.7% chord Max camber 5.1% at 39.7% chord Max Cl/Cd 101.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(goe479-il) GOE 479 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 479 airfoil Max thickness 11.6% at 30% chord Max camber 4% at 40% chord Max Cl/Cd 101.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s817-nr) NREL's S817 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S817 tip 16.0% Dia=30 to 50 m Re=3.0E+6 Clmax(S)=1.10 Clmax(R)=1.08 Restrained max lift coef Max thickness 16% at 51.1% chord Max camber 2.8% at 41.1% chord Max Cl/Cd 101.1 at Re# 500,000 Source NWTC National WInd Technology Center
(naca4412-il) NACA 4412		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 4412 airfoil Max thickness 12% at 30% chord Max camber 4% at 40% chord Max Cl/Cd 101.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(k3311sm-il) K3311 (smoothed)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Leon Kincaid K3311 airfoil (smoothed) Max thickness 11% at 30.6% chord Max camber 3.2% at 41.6% chord Max Cl/Cd 101.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(hq359-il) HQ 3.5/9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 3.5/9 R/C sailplane airfoil Max thickness 9% at 35% chord Max camber 3.5% at 50% chord Max Cl/Cd 101.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database