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.

(dae21-il) DAE-21 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela DAE21 low Reynolds number airfoil Max thickness 11.8% at 32% chord Max camber 6.6% at 43.7% chord Max Cl/Cd 45.9 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(eh2070-il) EH 2.0/7.0		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	John Yost EH 2.0/7.0 for tailless R/C aircraft Max thickness 7% at 28.7% chord Max camber 2% at 25.9% chord Max Cl/Cd 45.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(dormoy-il) Dormoy		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Dormoy airfoil Max thickness 9% at 30% chord Max camber 2.9% at 40% chord Max Cl/Cd 45.8 at Re# 100,000 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 Max Cl/Cd 45.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(cast102-il) CAST 10-2/DOA 2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CAST 10-2/DOA 2 transonic airfoil Max thickness 12.2% at 45.4% chord Max camber 1.5% at 69.4% chord Max Cl/Cd 45.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(naca632a015-il) NACA 63(2)A-015		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 63(2)A-015 airfoil Max thickness 15% at 37.1% chord Max camber 1.7% at 14.6% chord Max Cl/Cd 45.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(glennmartin2-il) Glenn Martin 2		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Glenn Martin 2 airfoil Max thickness 13.5% at 20% chord Max camber 6.1% at 30% chord Max Cl/Cd 45.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(rc08n1-il) NASA/LANGLEY RC-08(N)1 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NASA/Langley RC-08(N)1 rotorcraft airfoil Max thickness 8% at 37.5% chord Max camber 1.6% at 25% chord Max Cl/Cd 45.8 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(ag44ct02r-il) AG44ct -02f		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Drela AG44ct -02f airfoil Max thickness 7.3% at 24.6% chord Max camber 1.9% at 34.4% chord Max Cl/Cd 45.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(rg14a147-il) RG 14A-1.4/7.0 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rolf Girsberger RG 14A-1.4/7.0 airfoil Max thickness 7% at 29.7% chord Max camber 1.4% at 34.3% chord Max Cl/Cd 45.7 at Re# 100,000 Source UIUC Airfoil Coordinates Database