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.

(m7-il) NACA M7 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-7 airfoil Max thickness 6.2% at 40% chord Max camber 4.9% at 30% chord Max Cl/Cd 54.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(gs1-il) SIKORSKY GS-1 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gluharoff/Sikorsky GS-1 airfoil Max thickness 13.9% at 30% chord Max camber 4.1% at 50% chord Max Cl/Cd 54.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe314-il) GOE 314 (HANSA-BRANDENBURG) AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 314 (Hansa-Brandenburg) airfoil Max thickness 8% at 29.9% chord Max camber 4.7% at 29.9% chord Max Cl/Cd 54.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(clarky-il) CLARK Y AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK Y airfoil Max thickness 11.7% at 28% chord Max camber 3.4% at 42% chord Max Cl/Cd 54.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(clarkk-il) CLARK K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK K airfoil Max thickness 11.7% at 29.7% chord Max camber 3.3% at 39.6% chord Max Cl/Cd 54.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database

(mh120-il) MH 120 11.57%		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Martin Hepperle MH 120 for tip section of a propeller Max thickness 11.6% at 34.7% chord Max camber 2.2% at 44.2% chord Max Cl/Cd 54.1 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(clarkz-il) CLARK Z AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	CLARK Z airfoil Max thickness 11.8% at 30% chord Max camber 4% at 40% chord Max Cl/Cd 54 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(davis-il) Davis AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Consolidated/Davis airfoil (B-24 wing?) Max thickness 11.3% at 30% chord Max camber 3.7% at 40% chord Max Cl/Cd 54 at Re# 100,000 Source UIUC Airfoil Coordinates Database
(goe418-il) GOE 418 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 418 airfoil Max thickness 12.7% at 20% chord Max camber 5.1% at 40% chord Max Cl/Cd 54 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 54 at Re# 100,000 Source UIUC Airfoil Coordinates Database