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.

(ste87151-il) EPPLER STE 871-514 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler STE 871-514 airfoil Max thickness 13.9% at 47.3% chord Max camber 2.5% at 79% 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
(nlf416-il) NASA/LANGLEY NLF(1)-0416 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley/Somers NLF(1)-0416 natural laminar flow airfoil Max thickness 15.9% at 30.4% chord Max camber 2.5% at 34.8% chord Source UIUC Airfoil Coordinates Database
(sc20714-il) NASA SC(2)-0714 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA SC(2)-0714 airfoil (NASA TP-2969) Max thickness 14% at 37% chord Max camber 2.5% at 81% chord Source UIUC Airfoil Coordinates Database
(fauvel-il) FAUVEL 14% AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Fauvel 14% flying wing airfoil Max thickness 14% at 25.2% chord Max camber 2.5% at 25.2% chord Source UIUC Airfoil Coordinates Database
(raf38-il) RAF 38 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-38 airfoil Max thickness 12.7% at 30% chord Max camber 2.5% at 40% chord Source UIUC Airfoil Coordinates Database
(e212-il) E212 (10.55%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E212 low Reynolds number airfoil Max thickness 10.6% at 27.5% chord Max camber 2.5% at 61.3% chord Source UIUC Airfoil Coordinates Database
(mh201-il) MH 201 13.08%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 201 for a canard airplane (canard) Max thickness 13% at 38.1% chord Max camber 2.5% at 48.3% chord Source UIUC Airfoil Coordinates Database
(s3021-il) S3021-095-84		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S3021 low Reynolds number airfoil Max thickness 9.5% at 30% chord Max camber 2.5% at 39.2% chord Source UIUC Airfoil Coordinates Database
(e207-il) E207 (12.04%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E207 low Reynolds number airfoil Max thickness 12% at 29.6% chord Max camber 2.5% at 38.6% chord Source UIUC Airfoil Coordinates Database

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