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.

(goe409-il) GOE 409 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 409 airfoil Max thickness 12.7% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 37.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ebambino7-il) E. Bambino		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	E. Bambino airfoil Max thickness 6% at 40% chord Max camber 1.9% at 20% chord Max Cl/Cd 37.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(dga1182-il) D.G.A. 1182		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	D.G.A. 1182 airfoil Max thickness 7.6% at 30% chord Max camber 0.9% at 20% chord Max Cl/Cd 37.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(naca001035-il) NACA 0010-35		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0010-35 airfoil Max thickness 10% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 37.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(dsma523a-il) DSMA-523A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	McDonnell/Douglas DSMA-523 transonic airfoil with sharp trailing edge Max thickness 11% at 36% chord Max camber 2.3% at 82% chord Max Cl/Cd 37.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(ames02-il) NASA/AMES A-02 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/AMES/Hicks A-02 transonic rotorcraft airfoil Max thickness 7.7% at 30% chord Max camber 0.5% at 12.5% chord Max Cl/Cd 37.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(s1010-il) S1010 HPV airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1010 HPV airfoil Max thickness 6% at 23.3% chord Max camber 0% at 0% chord Max Cl/Cd 37.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(ea61012-il) EPPLER EA 6(-1)-012 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler EA 6(-1)-012 airfoil Max thickness 12% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 37.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(nlr7301-il) NLR-7301 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NLR NLR-7301 transonic airfoil Max thickness 16.5% at 35% chord Max camber 1.7% at 75% chord Max Cl/Cd 37.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx66s196-il) FX 66-S-196 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 66-S-196 airfoil Max thickness 19.6% at 37.1% chord Max camber 3.8% at 43.5% chord Max Cl/Cd 37.2 at Re# 200,000 Source UIUC Airfoil Coordinates Database