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.

(s1046-il) S1046 17% (Danny Howell)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig S1046 airfoil Max thickness 17% at 30.8% chord Max camber 0% at 0% chord Max Cl/Cd 80.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(m10-il) NACA M10 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-10 airfoil Max thickness 6.2% at 30% chord Max camber 1.9% at 30% chord Max Cl/Cd 80.9 at Re# 1,000,000 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 80.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca64a410-il) NACA 64A410		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64A410 airfoil Max thickness 10% at 39.9% chord Max camber 2.7% at 50% chord Max Cl/Cd 80.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(coanda3-il) Coanda 3		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Coanda 3 airfoil Max thickness 7% at 30% chord Max camber 2.9% at 40% chord Max Cl/Cd 80.9 at Re# 1,000,000 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 80.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(goe511-il) GOE 511 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 511 airfoil Max thickness 16.6% at 19.9% chord Max camber 8% at 29.8% chord Max Cl/Cd 80.9 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(naca64208-il) NACA 64-208		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 64-208 airfoil Max thickness 8% at 40% chord Max camber 1.1% at 50% chord Max Cl/Cd 80.8 at Re# 1,000,000 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 80.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database
(n63215-il) NACA 63-215 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(2)-215 airfoil Max thickness 15% at 34.9% chord Max camber 1.1% at 50% chord Max Cl/Cd 80.8 at Re# 1,000,000 Source UIUC Airfoil Coordinates Database