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.

(s827-nr) NREL's S827 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S827 primary 21.0% Dia=40 to 50 m Re=4.0E+6 Clmax(S)=1.00 Clmax(R)=0.99 Restrained max lift coef Max thickness 21% at 44.9% chord Max camber 2.2% at 68% chord Max Cl/Cd 81.3 at Re# 500,000 Source NWTC National WInd Technology Center
(mh46-il) MH 46 9.1%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 46 for flying wings Max thickness 9.1% at 27.1% chord Max camber 1.4% at 36.9% chord Max Cl/Cd 81.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e335-il) EPPLER 335 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E335 flying wing airfoil Max thickness 12.6% at 29% chord Max camber 2.3% at 19.9% chord Max Cl/Cd 81.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(ag38-il) AG38		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG38 airfoil Max thickness 7% at 27.7% chord Max camber 2% at 36.7% chord Max Cl/Cd 81.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e1233-il) EPPLER 1233 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E1233 general aviation airfoil Max thickness 18.9% at 29.8% chord Max camber 4.4% at 29.8% chord Max Cl/Cd 81.3 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(s834-nr) NREL's S834 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S834 tip 15.0% Dia=1 to 3 m Re=4.0E+5 Clmax(S)=1.00 Clmax(R)=1.02 High max lift coef Max thickness 15% at 39.5% chord Max camber 1.6% at 60% chord Max Cl/Cd 81.2 at Re# 500,000 Source NWTC National WInd Technology Center
(s809-nr) NREL's S809 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S809 primary 21.0% Re=2.0E+6 Clmax(S)=1.00 Restrained max lift coef Max thickness 21% at 39.5% chord Max camber 1% at 82.3% chord Max Cl/Cd 81.2 at Re# 500,000 Source NWTC National WInd Technology Center
(m9-il) NACA M9 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-9 airfoil Max thickness 10.4% at 15% chord Max camber 7.2% at 30% chord Max Cl/Cd 81.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fx60157-il) FX 60-157 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 60-157 airfoil Max thickness 15.7% at 40.2% chord Max camber 2.7% at 75% chord Max Cl/Cd 81.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(ag27-il) AG27 Bubble Dancer DLG by Mark Drela		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG27 airfoil used on the Bubble Dancer R/C DLG Max thickness 6.1% at 21.7% chord Max camber 2.6% at 44% chord Max Cl/Cd 81.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database