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.

(ls413mod-il) NASA/LANGLEY LS(1)-0413MOD 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)-0413MOD general aviation airfoil Max thickness 13% at 35% chord Max camber 2.2% at 40% chord Max Cl/Cd 66 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fg1-il) Fage & Collins 1		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Fage & Collins 1 airfoil Max thickness 8.2% at 30% chord Max camber 3.1% at 40% chord Max Cl/Cd 66 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(kc135c-il) KC-135 BL200.76 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing KC-135 transonic airfoils Max thickness 10.6% at 40% chord Max camber 1.5% at 25% chord Max Cl/Cd 66 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e550-il) EPPLER 550 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E550 general aviation airfoil Max thickness 18.2% at 34% chord Max camber 2.2% at 29.4% chord Max Cl/Cd 66 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e180-il) E180 (8.59%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E180 low Reynolds number airfoil Max thickness 8.6% at 33.5% chord Max camber 2% at 38.1% chord Max Cl/Cd 66 at Re# 200,000 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 66 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ag26-il) AG26 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 AG26 airfoil used on the Bubble Dancer R/C DLG Max thickness 6.8% at 23.3% chord Max camber 2.5% at 45.5% chord Max Cl/Cd 65.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(sd8040-il) SD8040 (10%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD8040 low Reynolds number airfoil Max thickness 10% at 29.7% chord Max camber 2.1% at 44% chord Max Cl/Cd 65.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s820-nr) NREL's S820 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S820 tip 16.0% Dia=10 to 20 m Re=1.3E+6 Clmax(S)=1.10 Clmax(R)=1.06 Restrained max lift coef Max thickness 16% at 45.1% chord Max camber 2.1% at 59.7% chord Max Cl/Cd 65.9 at Re# 200,000 Source NWTC National WInd Technology Center
(goe510-il) GOE 510 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 510 airfoil Max thickness 13.7% at 19.7% chord Max camber 5.8% at 39.7% chord Max Cl/Cd 65.9 at Re# 200,000 Source UIUC Airfoil Coordinates Database