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.

(cp-100-050-gn) Cambered plate C=10% T=5% R=1.3		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=10% Wall thickness=5% Radius=1.3 Max thickness 7% at 4.2% chord Max camber 7.9% at 46.5% chord Max Cl/Cd 50.8 at Re# 500,000 Source Generated
(naca001065-il) NACA 0010-65		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 0010-65 airfoil Max thickness 10% at 50% chord Max camber 0% at 0% chord Max Cl/Cd 50.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca66-018-il) NACA 66-018		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 66-018 airfoil Max thickness 18% at 45% chord Max camber 0% at 0% chord Max Cl/Cd 50.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe409-il) GOE 409 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 409 airfoil Max thickness 12.7% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 50.7 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(goe16k-il) GOE 16K AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 16K airfoil Max thickness 18.2% at 50% chord Max camber 4.1% at 50% chord Max Cl/Cd 50.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database

(goe460-il) GOE 460 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Gottingen 460 airfoil Max thickness 20.5% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 50.6 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(naca23021-il) NACA 23021		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 23021 airfoil Max thickness 21% at 30% chord Max camber 1.9% at 10% chord Max Cl/Cd 50.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(m1-il) NACA-M1 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA/Munk M-1 airfoil Max thickness 6.2% at 30% chord Max camber 0% at 0% chord Max Cl/Cd 50.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(n6h20-il) NACA 6-H-20 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	NACA 6-H-20 rotorcraft airfoil Max thickness 20% at 40% chord Max camber 6.1% at 40% chord Max Cl/Cd 50.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database
(fx2-il) WORTMANN FX 2 AIRFOIL		Airfoil details Send to airfoil plotter Add to comparison Lednicer format dat file Selig format dat file Source dat file
	Wortmann FX 2 airfoil Max thickness 20.4% at 43.5% chord Max camber 3.8% at 69.1% chord Max Cl/Cd 50.5 at Re# 500,000 Source UIUC Airfoil Coordinates Database