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.

(ag03-il) AG03 (flat aft bottom)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG03 (flat aft bottom) airfoil Max thickness 6.2% at 25.7% chord Max camber 2% at 33.1% chord Max Cl/Cd 46.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca2415-il) NACA 2415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 2415 airfoil Max thickness 15% at 30% chord Max camber 2% at 40% chord Max Cl/Cd 46.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(naca652415-il) NACA 65(2)-415		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65(2)-415 airfoil Max thickness 15% at 39.9% chord Max camber 2.2% at 50% chord Max Cl/Cd 46.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(n63210-il) NACA 63-210 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63-210 airfoil Max thickness 10% at 35% chord Max camber 1.1% at 60% chord Max Cl/Cd 46.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(giiig-il) GIII BL167 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 8.3% at 44.9% chord Max camber 1.3% at 29.9% chord Max Cl/Cd 46.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(ag11-il) AG11		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG11 airfoil Max thickness 5.8% at 26% chord Max camber 2.2% at 29.7% chord Max Cl/Cd 46.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e399-il) EPPLER 399 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E399 human powered aircraft airfoil Max thickness 14.8% at 29% chord Max camber 5.1% at 51.4% chord Max Cl/Cd 46.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(sd8000-il) SD8000-089-88		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Selig/Donovan SD8000 low Reynolds number airfoil Max thickness 8.9% at 29.4% chord Max camber 1.5% at 54% chord Max Cl/Cd 46.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(e328-il) EPPLER 328 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E328 flying wing airfoil Max thickness 13.3% at 31.5% chord Max camber 3% at 22.1% chord Max Cl/Cd 46.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(giiif-il) GIII BL145 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 8.3% at 44.9% chord Max camber 1.3% at 29.9% chord Max Cl/Cd 46.6 at Re# 100,000 Source UIUC Airfoil Coordinates Database