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.

(eh1590-il) EH 1.5/9.0		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	John Yost EH 1.5/9.0 for tailless R/C aircraft Max thickness 9% at 28.7% chord Max camber 1.5% at 25.9% chord Max Cl/Cd 60.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(m8-il) NACA M8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-8 airfoil Max thickness 11.7% at 15% chord Max camber 8% at 30% chord Max Cl/Cd 60.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s822-nr) NREL's S822 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S822 tip 16.0% Dia=2 to 10 m Re=6.0E+5 Clmax(S)=1.00 Clmax(R)=0.98 Restrained max lift coef Max thickness 16% at 39.2% chord Max camber 1.8% at 59.5% chord Max Cl/Cd 60.2 at Re# 200,000 Source NWTC National WInd Technology Center
(fx082512-il) WORTMANN FX 082-512 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 082-512 airfoil Max thickness 11.8% at 25% chord Max camber 4.2% at 62.9% chord Max Cl/Cd 60.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(goe344-il) GOE 344 (PFALZ 71) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 344 (Pfalz 71) airfoil Max thickness 7.2% at 19.9% chord Max camber 2.7% at 39.9% chord Max Cl/Cd 60.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(e341-il) EPPLER 341 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E341 flying wing airfoil Max thickness 13.9% at 32.8% chord Max camber 3% at 23.2% chord Max Cl/Cd 60.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(defcnd1-il) DEFIANT CANARD BL20 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rutan DEFIANT canard BL20 airfoil Max thickness 20.9% at 28.6% chord Max camber 4.5% at 36.1% chord Max Cl/Cd 60.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(mh81-il) MH 81 13%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 81 for flying wings (hang glider) Max thickness 12.9% at 25.4% chord Max camber 3.3% at 25.4% chord Max Cl/Cd 60.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e625-il) EPPLER 625 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E625 airfoil Max thickness 13% at 30% chord Max camber 2.9% at 22.5% chord Max Cl/Cd 60.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s823-nr) NREL's S823 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S823 root 21.0% Dia=2 to 10 m Re=4.0E+5 Clmax(S)=1.20 Clmax(R)=1.16 Restrained max lift coef Max thickness 21.2% at 24.3% chord Max camber 2.4% at 70.5% chord Max Cl/Cd 60 at Re# 200,000 Source NWTC National WInd Technology Center