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.

(isa960-il) I.S.A. 960		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	I.S.A. 960 airfoil Max thickness 9.5% at 30% chord Max camber 4.5% at 40% chord Max Cl/Cd 68.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(raf25-il) RAF 25 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	RAF-25 airfoil Max thickness 6.5% at 29.9% chord Max camber 1% at 49.9% chord Max Cl/Cd 68.2 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(amsoil1-il) RUTAN CANARD AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Rutan AMSOIL racer canard airfoil Max thickness 11.6% at 39% chord Max camber 2.1% at 42% chord Max Cl/Cd 68.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe417a-il) GOE 417A (GEW. PLATTE) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 417A (GEW. PLATTE) airfoil Max thickness 3.2% at 2.5% chord Max camber 5.9% at 40% chord Max Cl/Cd 68.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(npl9615-il) NPL 9615 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NPL 9615 rotorcraft airfoil Max thickness 11.3% at 34.2% chord Max camber 1% at 19.8% chord Max Cl/Cd 68.1 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(hq159b-il) HQ 1.5/9 B AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Quabeck HQ 1.5/9 B R/C sailplane airfoil Max thickness 9% at 37.1% chord Max camber 1.5% at 50% chord Max Cl/Cd 68 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(eiffel428-il) Eiffel 428 (Bleriot)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eiffel 428 (Bleriot) airfoil Max thickness 9% at 30% chord Max camber 4.2% at 40% chord Max Cl/Cd 68 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e168-il) E168 (12.45%)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E168 low Reynolds number airfoil Max thickness 12.4% at 26.7% chord Max camber 0% at 0% chord Max Cl/Cd 67.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fx76120-il) WORTMANN FX 76-120		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 76-120 symmetrical airfoil Max thickness 12.1% at 27.9% chord Max camber 0% at 0% chord Max Cl/Cd 67.9 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(e858-il) EPPLER 858 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E858 propeller airfoil Max thickness 22.7% at 26.6% chord Max camber 4.7% at 44.3% chord Max Cl/Cd 67.8 at Re# 500,000 Source UIUC Airfoil Coordinates Database