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.

(goe587-il) GOE 587 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 587 airfoil Max thickness 5.8% at 40% chord Max camber 3% at 30% chord Max Cl/Cd 77.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e169-il) E169 (14.4%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E169 low Reynolds number airfoil Max thickness 14.4% at 26.5% chord Max camber 0% at 0% chord Max Cl/Cd 77.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(clarkyh-il) CLARK YH AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK YH airfoil Max thickness 11.9% at 30% chord Max camber 2.5% at 30% chord Max Cl/Cd 77.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(v43012-il) BOEING VERTOL V43012-1.58 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol V43012-1.58 rotorcraft airfoil Max thickness 12% at 32% chord Max camber 3.7% at 15% chord Max Cl/Cd 77.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe676-il) GOE 676 (= M 12) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 676 (= M 12) airfoil Max thickness 11.9% at 30% chord Max camber 2% at 30% chord Max Cl/Cd 77.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(as5046-il) AS5046 (16%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	AS5046 airfoil Ashok Gopalarathnam/Selig 16% airfoil Max thickness 16% at 37.6% chord Max camber 0.7% at 77.4% chord Max Cl/Cd 77.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(atr72sm-il) Smoothed ATR airfoil coordinates obtained using AFSMO (Harry Morgan's NASA smoothing program)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	ATR 72 wing airfoil (from NTSB report) Max thickness 14.5% at 25.4% chord Max camber 2.9% at 21.4% chord Max Cl/Cd 77.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(clarym18-il) CLARK YM-18 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK YM18 airfoil Max thickness 18% at 29.6% chord Max camber 3.6% at 39.6% chord Max Cl/Cd 77.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e850-il) EPPLER E850 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E850 propeller airfoil Max thickness 8% at 36.6% chord Max camber 1.8% at 71% chord Max Cl/Cd 77.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(s819-nr) NREL's S819 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S819 primary 21.0% Dia=10 to 20 m Re=1.0E+6 Clmax(S)=1.20 Clmax(R)=1.16 Restrained max lift coef Max thickness 21.1% at 28.4% chord Max camber 1.3% at 77.3% chord Max Cl/Cd 77.6 at Re# 500,000 Source NWTC National WInd Technology Center