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.

(naca16021-il) NACA 16-021		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 16-021 airfoil Max thickness 21% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 26.3 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(cp-060-050-gn) Cambered plate C=6% T=5% R=2.11		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file
	HAWT pipe blade with coordinates based on top surface. Camber=6% Wall thickness=5% Radius=2.113 Max thickness 10.8% at 6.3% chord Max camber 2.7% at 52.1% chord Max Cl/Cd 26.1 at Re# 200,000 Source Generated
(naca16006-il) NACA 16-006		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 16-006 airfoil Max thickness 6% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 25.6 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(lnv109a-il) LNV109A		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Douglas/Liebeck LNV109A high lift airfoil Max thickness 13% at 23.5% chord Max camber 6% at 31.5% chord Max Cl/Cd 25.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(n66021-il) NACA 66-021 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66(4)-021 airfoil Max thickness 21% at 45% chord Max camber 0% at 0% chord Max Cl/Cd 25.5 at Re# 200,000 Source UIUC Airfoil Coordinates Database

(npl9510-il) NPL 9510 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NPL 9510 transonic airfoil Max thickness 11.1% at 32% chord Max camber 1.6% at 80% chord Max Cl/Cd 25.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(n5h20-il) NACA 5-H-20 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 5-H-20 rotorcraft airfoil Max thickness 19.9% at 40% chord Max camber 4.5% at 40% chord Max Cl/Cd 25.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(fx049915-il) WORTMANN FX 049-915 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 049-915 airfoil Max thickness 14.7% at 37.1% chord Max camber 5.8% at 37.1% chord Max Cl/Cd 25.4 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(la5055-il) LIEBECK LA5055 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Liebeck high lift airfoil Max thickness 15.9% at 35% chord Max camber 5.9% at 40% chord Max Cl/Cd 24.7 at Re# 200,000 Source UIUC Airfoil Coordinates Database
(e863-il) EPPLER 863 STRUT AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Eppler E863 strut airfoil Max thickness 35.7% at 28.5% chord Max camber 0% at 0% chord Max Cl/Cd 24 at Re# 200,000 Source UIUC Airfoil Coordinates Database