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.

(goe575-il) GOE 575 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 575 airfoil Max thickness 13.3% at 29.8% chord Max camber 3.6% at 39.8% chord Source UIUC Airfoil Coordinates Database
(hsnlf213-il) HSNLF(1)-0213 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley HSNLF(1)-0213 high speed natural laminar flow airfoil Max thickness 13.3% at 42.4% chord Max camber 1.4% at 32.4% chord Source UIUC Airfoil Coordinates Database
(mh82-il) MH 82 13.31%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 82 for flying wings (hang glider) Max thickness 13.3% at 24.6% chord Max camber 3.9% at 24.6% chord Source UIUC Airfoil Coordinates Database
(mh83-il) MH 83 13.29%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 83 for flying wings (hang glider) Max thickness 13.3% at 20.6% chord Max camber 4.5% at 32.6% chord Source UIUC Airfoil Coordinates Database
(usa27m2-il) USA 27 mod. AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-27MOD airfoil Max thickness 13.3% at 30% chord Max camber 5% at 40% chord Source UIUC Airfoil Coordinates Database
(usa40-il) USA 40 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	USA-40 airfoil Max thickness 13.3% at 30% chord Max camber 4.2% at 40% chord Source UIUC Airfoil Coordinates Database
(ah79k132-il) AH 79-K-132/20		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 79-K-132/20 airfoil for use with flaps (K) Max thickness 13.2% at 40.2% chord Max camber 3.7% at 40.2% chord Source UIUC Airfoil Coordinates Database
(ah93k132-il) AH 93-K-132/15		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 93-K-132/15 airfoil for use with flaps (K) Max thickness 13.2% at 41.2% chord Max camber 3.5% at 41.2% chord Source UIUC Airfoil Coordinates Database
(goe404-il) GOE 404 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 404 airfoil Max thickness 13.2% at 29.6% chord Max camber 5% at 29.6% chord Source UIUC Airfoil Coordinates Database
(goe411-il) GOE 411 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 411 airfoil Max thickness 13.2% at 30% chord Max camber 0% at 0% chord Source UIUC Airfoil Coordinates Database

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