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.

(ah85l120-il) AH 85-L-120/17		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Althaus AH 85-L-120/17 symmetrical airfoil Max thickness 12.1% at 43.5% chord Max camber 0% at 0% chord Max Cl/Cd 27.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(bqm34-il) RYAN BQM-34 FIREBEE WING AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Ryan BQM-34 Firebee wing airfoil (NACA 63-014A W/NACA 0014 nose and thinned to .09899 to account for sweep) Max thickness 9.9% at 32.5% chord Max camber 0% at 0% chord Max Cl/Cd 27.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(n64012-il) NASA/LANGLEY 64-012 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64(1)-012 airfoil Max thickness 12% at 40% chord Max camber 0% at 0% chord Max Cl/Cd 27.1 at Re# 50,000 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 Max Cl/Cd 27.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(s805a-nr) NREL's S805A Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S805A primary Max thickness 13.5% at 40% chord Max camber 2.1% at 35% chord Max Cl/Cd 27.1 at Re# 50,000 Source NWTC National WInd Technology Center

(r140-il) R140 (original)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	R140 Quickee 500 airfoil (original) Max thickness 12% at 39.3% chord Max camber 0.5% at 42.3% chord Max Cl/Cd 27.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(n11-il) N-11		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	N-11 airfoil Max thickness 10.9% at 30% chord Max camber 4.4% at 40% chord Max Cl/Cd 27.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(v43015-il) BOEING VERTOL V43015-2.48 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Boeing-Vertol V43015-2.48 rotorcraft airfoil Max thickness 15% at 30% chord Max camber 3.7% at 15% chord Max Cl/Cd 27.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(lwk79100-il) LWK 79-100		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	LWK 79-100 symmetrical airfoil Max thickness 10% at 27.9% chord Max camber 0% at 0% chord Max Cl/Cd 27.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(e331-il) EPPLER 331 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E331 flying wing airfoil Max thickness 11.2% at 28.3% chord Max camber 2.7% at 23.6% chord Max Cl/Cd 27.1 at Re# 50,000 Source UIUC Airfoil Coordinates Database