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.

(mh110-il) MH 110 10.01%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 110 for stall controlled wind turbines (tip) Max thickness 10% at 23.9% chord Max camber 1% at 15.8% chord Max Cl/Cd 39 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(rae101-il) RAE 101 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAE 101 airfoil Max thickness 10% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 39 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(n12-il) N-12		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	N-12 airfoil Max thickness 10.5% at 30% chord Max camber 0.2% at 15% chord Max Cl/Cd 39 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe741-il) GOE 741 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 741 airfoil Max thickness 15.3% at 30% chord Max camber 4.8% at 30% chord Max Cl/Cd 39 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(n64108-il) NACA 64-108 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64-108 airfoil Max thickness 8% at 40% chord Max camber 0.6% at 50% chord Max Cl/Cd 39 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(ultimate-il) ULTIMATE		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Carl Goldberg R/C Ultimate Bipe airfoil Max thickness 12.8% at 34.2% chord Max camber 0% at 0% chord Max Cl/Cd 39 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(nlr1t-il) NLR-1T AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Bell/NASA/NLR NLR-1T rotorcraft airfoil Max thickness 8.7% at 38.3% chord Max camber 1.3% at 22.3% chord Max Cl/Cd 38.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(giiia-il) GIII BL0 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Grumman/Gulfstream GIII transonic airfoils Max thickness 11% at 39.7% chord Max camber 0.7% at 14.7% chord Max Cl/Cd 38.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ag47ct02r-il) AG47ct -02f rot.		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG47ct -02f airfoil Max thickness 5% at 22.5% chord Max camber 1.2% at 33.4% chord Max Cl/Cd 38.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(sc2110-il) SIKORSKY SC2110 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Sikorsky/Lednicer & Owen SC2110 rotorcraft airfoil (SC5410) Max thickness 9.9% at 37.7% chord Max camber 1.9% at 15.7% chord Max Cl/Cd 38.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database