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.

(sc20402-il) NASA SC(2)-0402 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0402 airfoil (NASA TP-2969) Max thickness 2% at 34% chord Max camber 0.5% at 83% chord Max Cl/Cd 20.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(chen-il) CHEN AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	University of Illinois at Urbana-Champaign / Chen high lift airfoil Max thickness 12.5% at 27.7% chord Max camber 7.8% at 25.4% chord Max Cl/Cd 19.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(th25816-il) TH 25816 HALE AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Naval Air Development Center/Doug Hall high altitude Max thickness 25.7% at 48.3% chord Max camber 4% at 52.9% chord Max Cl/Cd 19.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(gu255118-il) UNIVERSITY OF GLASGOW GU25-5(11)8 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	University of Glasgow GU 25-5(11)8 canard airfoil (Quickie Max thickness 20% at 40% chord Max camber 7.1% at 45% chord Max Cl/Cd 17.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(kenmar-il) KENNEDY AND MARSDEN AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	University of Alberta/Kennedy and Marsden high lift airfoil Max thickness 27.9% at 31% chord Max camber 7.7% at 36.9% chord Max Cl/Cd 17.1 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(marsden-il) Marsden		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Marsden airfoil Max thickness 27.9% at 31.6% chord Max camber 7.7% at 37.6% chord Max Cl/Cd 17 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(n6h20-il) NACA 6-H-20 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 6-H-20 rotorcraft airfoil Max thickness 20% at 40% chord Max camber 6.1% at 40% chord Max Cl/Cd 16.8 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(jn153-il) JN-153 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Narramore JN153 airfoil Max thickness 17.6% at 28.2% chord Max camber 8.4% at 38.1% chord Max Cl/Cd 16.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(strand-il) STRAND AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Strand high lift airfoil Max thickness 15.4% at 26.1% chord Max camber 4.1% at 32.1% chord Max Cl/Cd 15.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx77w270-il) FX 77-W-270		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 77-W-270 airfoil for use on wind turbines (W) Max thickness 27.1% at 33.9% chord Max camber 4.3% at 27.9% chord Max Cl/Cd 15.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database