Airfoil Tools
Search 1638 airfoils

You have 0 airfoils loaded.
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.

(n24-il) N-24		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	N-24 airfoil Max thickness 17% at 30% chord Max camber 5.4% at 40% chord Source UIUC Airfoil Coordinates Database
(ms317-il) NASA/LANGLEY MS(1)-0317 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley MS(1)-0317 general aviation airfoil Max thickness 17% at 37.5% chord Max camber 1.7% at 72.5% chord Source UIUC Airfoil Coordinates Database
(mh102-il) MH 102 16.99%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 102 for stall controlled wind turbines (root) Max thickness 17% at 27.7% chord Max camber 2.8% at 37.6% chord Source UIUC Airfoil Coordinates Database
(ls417mod-il) NASA/LANGLEY LS(1)-0417MOD AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley LS(1)-0417MOD general aviation airfoil Max thickness 17% at 30.2% chord Max camber 2.3% at 20.2% chord Source UIUC Airfoil Coordinates Database
(ls417-il) NASA/LANGLEY LS(1)-0417 (GA(W)-1) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley/Whitcomb LS(1)-0417 (GA(W)-1) general aviation airfoil Max thickness 17% at 40% chord Max camber 2.4% at 65% chord Source UIUC Airfoil Coordinates Database

(goe449-il) GOE 449 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 449 airfoil Max thickness 17% at 30% chord Max camber 5.4% at 40% chord Source UIUC Airfoil Coordinates Database
(fx67k170-il) FX 67-K-170/17 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 67-K-170/17 airfoil Max thickness 17% at 40.2% chord Max camber 5.1% at 43.5% chord Source UIUC Airfoil Coordinates Database
(nn7mk20-il) NN7 MK20		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NN7 MK20 airfoil Max thickness 16.9% at 37.1% chord Max camber 3% at 59.8% chord Source UIUC Airfoil Coordinates Database
(goe423-il) GOE 423 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 423 airfoil Max thickness 16.9% at 39.7% chord Max camber 5.1% at 39.7% chord Source UIUC Airfoil Coordinates Database
(e561-il) EPPLER 561 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E561 general aviation airfoil Max thickness 16.9% at 27.9% chord Max camber 5.1% at 45.8% chord Source UIUC Airfoil Coordinates Database