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.

(marske4-il) MARSKE PIONEER IID TIP AIRFOIL (NACA 431012A*.833 HYBRID)		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Marske Pioneer IID tip airfoil (NACA 43012A*.833 hybrid) Max thickness 10.2% at 20% chord Max camber 2.8% at 15% chord Max Cl/Cd 22.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca661212-il) NACA 66(1)-212		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66(1)-212 airfoil Max thickness 12% at 45% chord Max camber 1.1% at 50% chord Max Cl/Cd 22.3 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(p51htip-il) NACA 66		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66 Max thickness 12% at 45% chord Max camber 1.3% at 47.5% chord Max Cl/Cd 22.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(goe648-il) GOE 648 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 648 airfoil Max thickness 15.2% at 29.4% chord Max camber 3.9% at 39.4% chord Max Cl/Cd 22.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(m21-il) NACA M21 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-21 airfoil Max thickness 12% at 30% chord Max camber 6% at 30% chord Max Cl/Cd 22.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database

(s804-nr) NREL's S804 Airfoil		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source file
	NREL HAWT airfoil S804 root Not recommended Max thickness 17.9% at 26.7% chord Max camber 4.2% at 39.6% chord Max Cl/Cd 22.2 at Re# 50,000 Source NWTC National WInd Technology Center
(falcon-il) Falcon		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Falcon airfoil used on the Carl Goldberg Falcon 56 Mk II R/C powerplane Max thickness 13.7% at 30.6% chord Max camber 1.6% at 20.5% chord Max Cl/Cd 22.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(joukowsk-il) 12% JOUKOWSKI AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	12% Joukowski airfoil Max thickness 11.8% at 25% chord Max camber 0% at 9.5% chord Max Cl/Cd 22.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(stf86361-il) EPPLER STF 863-615 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler STF 863-615 airfoil Max thickness 14.7% at 44.7% chord Max camber 4.2% at 72.3% chord Max Cl/Cd 22.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database
(naca65206-il) NACA 65-206		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 65-206 airfoil Max thickness 6% at 40% chord Max camber 1.1% at 50% chord Max Cl/Cd 22.2 at Re# 50,000 Source UIUC Airfoil Coordinates Database