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.

(e591-il) E591		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E591 airfoil Max thickness 15.7% at 25% chord Max camber 6% at 52.3% chord Source UIUC Airfoil Coordinates Database
(e855-il) EPPLER 855 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E855 propeller airfoil Max thickness 15.7% at 32.2% chord Max camber 3.7% at 50.6% chord 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 Source UIUC Airfoil Coordinates Database
(la203a-il) DOUGLAS LA203A AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Douglas/Liebeck LA203A high lift airfoil Max thickness 15.7% at 34.3% chord Max camber 5.5% at 46% chord Source UIUC Airfoil Coordinates Database
(fx63158-il) FX 63-158 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 63-158 airfoil Max thickness 15.8% at 33.9% chord Max camber 3.8% at 37.1% chord Source UIUC Airfoil Coordinates Database

(fxs21158-il) FX S 02/1-158 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX S 02/1-158 airfoil Max thickness 15.8% at 30.9% chord Max camber 3.5% at 37.1% chord Source UIUC Airfoil Coordinates Database
(goe627-il) GOE 627 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 627 airfoil Max thickness 15.8% at 30% chord Max camber 4.1% at 30% chord Source UIUC Airfoil Coordinates Database
(mh95-il) MH 95 15.86%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 95 parafoil Max thickness 15.8% at 33.6% chord Max camber 0.9% at 81.6% chord Source UIUC Airfoil Coordinates Database
(ah83159-il) AH 83-159		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 83-159 airfoil Max thickness 15.9% at 40.2% chord Max camber 3.8% at 40.2% chord Source UIUC Airfoil Coordinates Database
(davis-corrected-il) DAVIS BASIC B-24 WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Davis basic B-24 wing airfoil Max thickness 15.9% at 29.6% chord Max camber 2.5% at 29.6% chord Source UIUC Airfoil Coordinates Database